Department of Transportation

Vol. 81 Friday, No. 98 May 20, 2016

Part II

Federal Aviation Administration 14 CFR Part 60 Flight Simulation Training Device Qualification Standards for Extended Envelope and Adverse Weather Event Training Tasks (Correction); Final Rule

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DEPARTMENT OF TRANSPORTATION March 30, 2016, make the following corrections: Federal Aviation Administration ■ 1. Correct the table appearing on page 14 CFR Part 60 18240 to read as follows: [Docket No.: FAA–2014–0391; Amdt. No. 60—4] RIN 2120–AK08

Flight Simulation Training Device Qualification Standards for Extended Envelope and Adverse Weather Event Training Tasks Correction 14 CFR PART 60 [CORRECTED] In FR Rule Doc. No. 2016–05860 beginning on page 18178 in the issue of

TABLE A1B—TABLE OF TASKS VS. SIMULATOR LEVEL

QPS Requirements Information Subjective requirements Simulator Entry No. In order to be qualified at the simulator qualification level indi- levels cated, the simulator must be able to perform at least the Notes tasks associated with that level of qualification A B C D

******* 3. Inflight Maneuvers.

******* 3.b. High Angle of Attack Maneuvers 3.b.1 ...... Approaches to Stall ...... X X X X 3.b.2 ...... Full Stall ...... X X Stall maneuvers at angles of attack above the activation of the stall warning system. Required only for FSTDs qualified to conduct full stall training tasks as indicated on the Statement of Qualifica- tion.

******* 3.g...... Upset Prevention and Recovery Training (UPRT) ...... X X Upset recovery or unusual attitude training maneuvers within the FSTD’s validation envelope that are intended to exceed pitch attitudes greater than 25 degrees nose up; pitch attitudes greater than 10 degrees nose down, and bank angles greater than 45 degrees.

*******

■ 2. Correct the table appearing on pages 18242–18282 to read as follows:

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00014 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.011 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32029 an an this Figure Figure critically critically of for for 4 A A reference reference see see and and the the of of Notes paragraph systems, systems, Appendix Appendix to of of overdamped overdamped INFORMATION illustration illustration damped damped measurement. measurement. For Refer For A2B A2B Attachment. D c X X X X X X B Level Simulator A state. at at before rate). s ILS ILS rate). exhibit 5 until until Tests directions. load flight an an control both of roll pitch on on throw). that for both input. input. minor minor displacement before before 2°/S 2°/S in direction. full s s of of to to 5 5 of test minimum control control non-normal airplanes 0.5 0.5 maneuvering a control demonstrate deflection Ob_jective established established from from 50% of of typical typical opposite be to and For Test the to be be Details data data by the while while behavior, normal used must to 25% (FFS) must must is controller normal initiation initiation for directions. made made direction. in history history there limited be test roll (approximately (approximately after after inputs inputs reversal one both s s Test time time must 5 5 in in single a Show Show least least Test Test corrections corrections directions, control Control conditions approach Control envelope). allowable CCA: approach (approximately non-symmetrical Data If Simulator Flight and landing. Landing. Full or or Cruise, Flight REQUIREMENTS Conditions A2A- Takeoff, Approach Approach Landing. QPS or Table rate roll rate body time pitch body roll throughout peak the applied of peak body body 2.b.l. history. of as rate Tolerance applied time ±20% Same pitch rate history. or ±0.15°/s ±0.15°/s ±20% throughout the Inputs Inputs Title Control Control Control. Test Small Small Yaw -Pitch. -Roll. Entry Number 2.b.3. 2.b.4. 2.b.5.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00015 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.012 32030 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Notes INFORMATION D c X X B Level Simulator X X X X A a at before for a level the ILS rate). be 5 s or to until Tests an control control both of completion yaw on before must input. response go-around minor the before 2°/s 5 s direction. reversal or of to approach free to 5 s there minimum least for non-normal control non-normal 0.5 a demonstrate Ob_jective at established from control of typical change opposite be to to and and Test to be thrust Details continuous data the directions, while used used must before uncontrolled to power equal (FFS) must is is from normal normal initiation of change 5 s both directions. the in made in history there test test of (approximately of direction. after maximum inputs reversal both s change Test Test power time to history 5 s. increment in single single the a a 15 Show initiation Time corrections Test control demonstrate opposite directions, least CCA: CCA: of flight approach Control state. state. power. time minimum Power If If + Simulator Flight landing. Full or specified. Flight REQUIREMENTS Conditions A2A- Approach. Approach QPS otherwise Table unless rate pitch body of altitude. time yaw flight peak the of applied body ±20% level (100ft) or airspeed. Tolerance rate for kt ±20% angle. history. or ±0.15°/s ±3 ±30m ±1.5° yaw throughout Tests. required that Inputs Control is Title setting Change Control Test Small Power Power Dynamics. Longitudinal -Yaw. Entry Number 2.c. 2.c.l. 2.b.6.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00016 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.013 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32031 Notes INFORMATION D c B Level Simulator X X X X X X X X X X X X X X X X A s. a a a level s. 15 tests. for for for the 15 for the the to control control control control to to control and before before before thrust snapshot change+ response response response change+ change change 5 s 5 s 5 s of change change with free free free least least least non-normal non-normal non-normal non-normal extension series trim Objective Tests non-normal at at at a and and and and or Test to to to be both Details level configuration configuration reconfiguration for uncontrolled uncontrolled uncontrolled configuration configuration reconfiguration may equal equal equal (FFS) the the the normal normal normal normal normal of of of wings the the the of of of in in in in test in of of of applicable. required Test Test Test Test as This Test history history history s. increment increment increment 15 Steady-state Time Time Time completion completion completion initiation initiation initiation flight. CCA: CCA: CCA: CCA: CCA: mode mode mode mode mode, retraction. time time time Results + Simulator and and Flight initial and landing. Full (extension). to (retraction), through Flight Approach, REQUIREMENTS retraction, Conditions A2A- Takeoff Takeoff flap Cruise. Cruise, approach Approach Landing. QPS Table trim pitch pitch pitch or or of of of altitude. altitude. altitude. angle. thrust angle. ±20% ±20% ±20% net angle. (100ft) (100ft) (100ft) stabilizer or or or airspeed. airspeed. airspeed. of Tolerance m m m elevator pitch 5o kt kt kt o o angle. angle. angle. surface ±3 ±5% ±0. ±3 ±3 ±I ±1.5° ±1.5° ±I ±30 ±1.5° ±30 ±30 Trim. Change Dynamics. Title Change Test Spoiler/Speedbrake Flap/Slat Dynamics. Dynamics. Longitudinal Gear Change Entry Number 2.c.2. 2.c.3. 2.c.4. 2.c.5.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.015 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32033 to in the may due for test g at other based pilot have (some on at peak weights buffet or airplane lateral be stall trend data the conduct 0.03 to the flight to limit peak). to for at and limited limitations. and testing. based tasks. to amplitude on larger to engineering is a may conducted correct normal stall above perception where noise buffet buffet flight required only relative sponsor/FSTD Notes acceleration peak be buffet data buffet gravity based system validation of normal with required is of manufacturers g training peak qualified of of platform be for may Initial initial value to 0.1 seat test FSTD stall normal instances safety INFORMATION certification considerations, centers capability/limitations airframe acceleration. acceleration simulator speed should simulator seat. peak background pilot used peak maximum manufacturer motion Demonstrate FSTDs growth The Tests In This on full from threshold typically to validation D c B Level Simulator A of only in 25° to the is "g of correct loss proper for buffet, landing or (required a least 7 system. flight. flight recorded past or this Tests or the control required angle at testing second be use the off in initial necessary conducted three the of envelope of change airplanes The normal be roll must and g) must mode the a condition of occur to demonstrate aircraft) characteristic. range approach stall applicable (I stall) required information of Attachment flight satisfy must data demonstrate non-normal the attitude not this signal must to and Ob_jective must with and one See operation level normal attack driven FSTDs and are Test must condition than recovery but of pitch power-on exhibiting the Details used history turning least configuration. a signal wings condition at aircraft be correct sources (accelerated warning in (FFS) in flight at angle normal recovery. in setting Time attack, propeller demonstrate the sudden through in authority data may an stall tolerances flight CCA buffet/stall. a of systems, requirements (clean) airplanes angle for entry entry flap warning entry climb to to the of stall must Test For ranges. tests condition. through angle bank only cruise stall control Stall Stall Stall full applicable. flaps-up . . . concerning The These different flight additional a demonstrate conditions: characteristic. if demonstrated for The exhibiting CCA: attack segment states. stall relation break" protection required trend roll FSTDs Record Simulator Numerical and Flight Cruise Landing Full or Condition), Flight REQUIREMENTS Performance Altitude Conditions A2A- (Near Approach High Limited QPS for Table be stall: rate Nz those to control of initial (see must attack attack; attack; roll up and for and stall stall: upon 7) of of of and demonstrate angle; angle; angle equipped and for with flight pusher to rate. and or inputs trend and trend based threshold angle angle angle bank pitch pitch Required Break warning stick Tolerance yaw correct and and and component. systems speeds. simulators Stall Stall SOC plotted buffet buffet perception magnitude. magnitude reversible Recovery: Attachment Control Correct ±2.0° ±2.0° ±2.0° ±2.0° ±2.0° with Additionally, ±2.0° Approach warning Title Test Entry Number

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00021 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.018 32036 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations a of in trim to to for level test thrust. abruptly test for seconds that travel. condition. trained approximately to performed 10 controller is bank, climb landing response. takeoff thrust be allow Notes of or at failure at roll free pilot similar controller and be be a 30° reaching the should segment to roll engine INFORMATION airplane approximately an should should When return neutral manner 20° 2nd Test flight. the Approach which D c X X X B Level Simulator X X X X X X X X X X X X A of may roll off. 25% Tests a control control tests and control mode. with tests. on stability tum multiple lateral control with non-normal non-normal Ob_jective approximately snapshot from 30°. steady show at and and Test of a Details cycles augmentation test, throw. input six (FFS) non-normal normal normal averaged consist directions. in in step in maintain pedal least a stability data may to approximately at both Test Test Test alternative of test for for with with rudder an used. Test Test Test This Test angle CCA: CCA: full CCA: be As mode mode Airplane required Simulator or or Flight Climb, or Landing. Approach Approach Full or Segment Flight and and REQUIREMENTS Conditions Approach A2A- Second Cruise, and Cruise, Approach Landing. Landing. QPS o or 20 Table o ±I in ±2° used: yaw ±2 or of is of and and angle. angle equivalent 0% test angle or ±I roll ±10% trend angle. trend pedal. or of or s Tolerance side-slip rudder angle o alternate correct aileron s. rate. rudder If Correct ±10% ±I ±2°/s ±0.5 ±2° tab Response. Inoperative Title Roll Stability. Test Spiral Rudder Dutch Engine Trim. Entry Number 2.d.4. 2.d.5. 2.d.6. 2.d.7.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00026 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.023 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32041 B this this and of of 5 additional 5 information for Notes Level A to paragraph Attachment INFORMATION information. appendix for simulators. See See related Attachment D c X X X X X X X X X X X Level Simulator A B of using thrust training or pedal Tests appendix recovery reached. control thrust is input justification this rudder directions full provide of recognize operating execute with 5 speed. speed pedal with both that to to the in procedures. non-normal Ob.iective on reaching and or Test rudder and needed models provided input heading Details operating operation until thrust be Attachment (FFS) skills normal pedal See thrust in must maximum phenomena maintain reverse applicable. windshear tolerances, minimum minimum rudder Test as specific until full reverse tests, the rationale input in for full engine(s), CCA: reverser procedures. mode, reverser windshear Apply results. A Requires With Simulator Fli2ht Landing. Full and Flight REQUIREMENTS Conditions A2A- Takeoff Landing. Landing. Landing. QPS Table this Functions. of or 5 ±10% angle. or angle. angle. thrust rate. ft) angle. Protection net (5 stabilizer yaw airspeed. airspeed. airspeed. of m Tolerance elevator pitch heading AOA. Attachment kt kt kt height. o o equivalent. of ±2°/s ±5 ±3° ±5% ±0.5° ±1° ±1.5 ±1 ±1 ±5 ±3 See appendix. Envelope and of in active other one control control two the two models. Effect. with Effect. effectiveness) effectiveness) thrust. thrust. and and demonstrate Title Maneuver shear. tests, conducted asymmetric symmetric windshear to air demonstrate Test Ground (rudder (rudder still reverse reverse Directional Four Flight Directional landing, Test Ground each with with with windshear to takeoff Wind Entry Number 2.e.9. 2.g. 2.e.8. 2.h. 2.f.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00027 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.024 32042 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations and for onset as and on attack must power control of such angle attitude warning buffet control effects evaluated thrust/power Stall inputs acceleration stall Altitude Airspeed Angle Pitch Bank Flight Engine Normal Notes be attack, aerodynamic parameters and of will parameters • • • • • • • • • INFORMATION include: inputs, angle settings. representative relevant Plotted Tests other D c X X X X X X X X X X X X X X X X X X X X B Level Simulator A is in- and must as the by ice data effects of jUnction response relative as Test include, engine of effects of demonstrate type: 2.j. their caused icing demonstrate may if attack without the will demonstrate initiation accretion of results validation model(s) will to moment effects Section effectiveness test airplane states ice and effects test following test demonstrate Statement angle icing Objective Tests of history to One the stall Test describes AlA, Icing the performance control stall Flight Details intended control pitching to, second full Time in in that effects particular in required a are (FFS) Table test. effects. aerodynamic the utilize required the of in the limited baseline to and in are Tests accretion. degraded icing must rationale Changes Decrease Decrease not airplanes. baseline demonstrated. ice history • • • tests and test required. are aerodynamic FSTDs the The Time include Two described applicable flight Compliance accretion, airframe being but representative recovery. the not to the Simulator jUnction. normal or with Flight Climb, and and protection (i.e. or computer-controlled on Landing. condition- Full to Approach or (ice Cruise, Cruise. or Segment Flight Approach. envelope REQUIREMENTS jUnction flight Conditions tests Approach the A2A- [One Second applicable Takeoff Takeoff, Takeoff, oft)] Cruise, and Cruise. Approach Approach. two Landing Landing. QPS reach protection only to Table are angle factor 2.h envelope attack load required bank of of angle as each ±10% normal angle pitch airspeed. airspeed. Tolerance into thrust or kt kt Set ±3 ±O.lg ±5 ±1.5° ±2° ±1.5° requirements entry Icing Effects The during - required. (High Airframe are Airframe Note. Speed. inputs Attack. Attack) and and Title of of Angle. Angle. Factor. Effects control different) Test is to Demonstration Minimum Pitch Bank Engine Load Engine Icing Overspeed. Angle Angle Entry Number 2.h.6. 2.h.l. 2.h.2. 2.h.3. 2.h.4. 2.h.5. 2.i. 2.i.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00028 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.025 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32043 as this be (in of this from this 3 can system this this of perform with of of to 6 6 6.c. operating software subjective changes baseline motion Notes on qualified. and Attachment FSTD that continue to paragraph paragraph paragraph original INFORMATION information. See See See hardware readily identified normal mode) Refer Ensure Performance originally Attachment. Attachment. Attachment. Appendix testing. the D c Level Simulator X X X X X X X X X X X X X X X X A B and be to smooth ice Tests the tested) in expected required required reduction/variation, being characteristics forces aircraft where Objective perception buffet (power the Test etc. of scenario Details control demonstrate demonstrate drag on stall in to to in in (FFS) effects test test accretion present vibration, threshold response. Changes Change Engine Increase • • • • frequency Appropriate Appropriate tum-around. Simulator Flight Full Flight REQUIREMENTS applicable. applicable. Conditions A2A- Not Not None. QPS Table the the platform by by FSTD FSTD actual for for g accelerations. Tolerance specified specified linear ±0.05 qualification. qualification. sponsor sponsor As As repeatability. fidelity check. response. cueing effects. system system Title Test repeatability Frequency Motion Motion Motion Motion Turn-around System. Motion Entry Number 3.a. 3. 3.b. 3.c 3.e. 3.d.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00038 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.035 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32053 and of in into ft), scene be effects the RVR. taken representative night correctly of (1,200 tolerance The thermal may to be sm) Notes will the scene day (1 350m a scene m should Note.- scene alignment both b.l INFORMATION 1,609 characteristics demonstrated during the represent Visual removed. account. Infra-red 4. The of transition. D c X X X X X X X X Level Simulator X X X X A B the pilot a Tests to impacting modeling items presented localizer Ob.iective assess scene Test and to Details approach. visual (FFS) (GIS) ILS include: the designed an of is slope on items test glide RVR/Visibility; DH 1) at accuracy 2) These This Simulator m on zone Fli2ht an ft. 30m landing height at and at of300 350m the 200 Full or in at - night. slope point wheel Flight ft) ft). REQUIREMENTS touchdown setting ft) and Conditions glide 00 A2A above configuration approach (1 (1,000 (1,200 RVR Flight. Day Flight. Takeoff on Trimmed QPS of be the Table m with must out the during must of 350m and 1,609 correct align aircraft alignment thermal the including intensity. transition. image at type. between approach represents VGS VGS. the effects the and roll the ±20% of instruments. light of ft) RVR night display view within and end: Tolerance scene system to end: window sm) computed crossover day computed correct (1 and aircraft (1,200 number represent the Far Demonstrate Pitch EFVS EFVS The lights visible. Alignment typical Near and segment versus test. Flight calibration. (pitch crossover. (VGS). Title ground System ground horizon). attitude RVRand attitude of Test Enhanced indicator Thermal (EFVS) segment Visual Visual Vision visibility roll FSTD Registration HUD EFVS Entry Number 4.d 4.c.2 4.c.l 4.d.1 4.b.3 4.c.3 4.c

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■ 3. Correct the tables appearing on pages 18284–18300 to read as follows:

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

1-o Simulator Level -="~ a Operations Tasks ~ = z A B c D Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List or the level of simulator qualification involved. Items not installed or not functional on the simulator and, therefore, not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ. 1. Preparation For Flight l.a. Pre-flight. Accomplish a functions check of all switches, indicators, systems, and equipment at all crew members' and instructors' stations and determine that: l.a.l The flight deck design and functions are identical to that of the X X X X airplane being simulated. l.a.2 Reserved l.a.3 Reserved 2. Surface Operations (pre-flight). 2.a. En2ine Start 2.a.l. Normal start X X X X 2.a.2. Alternate start procedures X X X X 2.a.3. Abnormal starts and shutdowns (e.g., hot/hung start, tail pipe X X X X fire) 2.b. Taxi 2.b.1 Pushback/powerback X X X 2.b.2. Thrust response X X X X 2.b.3. Power lever friction X X X X 2.b.4. Ground handling X X X X 2.b.5. Nosewheel scuffing X X 2.b.6. Taxi aids (e.g. taxi camera, moving map) X X 2.b.7. Low visibility (taxi route, signage, lighting, markings, etc.) X X 2.c. Brake Operation 2.c.l. Brake operation (normal and alternate/emergency) X X X X 2.c.2. Brake fade (if applicable) X X X X 2.d Other 3. Take-off. 3.a. Normal 3.a.l. Airplane/engine parameter relationships, including run-up X X X X 3.a.2. Nosewheel and rudder steering X X X X 3.a.3.a Crosswind (maximum demonstrated) X X X X 3.a.3.b Gusting crosswind X X 3.a.4. Special performance 3.a.4.a Reduced V1 X X X X 3.a.4.b Maximum engine de-rate X X X X 3.a.4.c Soft surface X X 3.a.4.d Short field/short take-off and landing (STOL) operations X X X X

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

1-o t>~ Simulator Level ..... a Operations Tasks ~= = z A B c D 3.a.4.e Obstacle (performance over visual obstacle) X X 3.a.5. Low visibility take-off X X X X 3.a.6. Landing gear, wing flap leading edge device operation X X X X 3.a.7. Contaminated runway operation X X 3.a.8. Other 3.b. Abnormal/emergency 3.b.l. Rejected Take-off X X X X 3.b.2. Rejected special performance (e.g., reduced Vt, max de-rate, X X X X short field operations) 3.b.3. Rejected take-off with contaminated runway X X 3.b.4. Takeoff with a propulsion system malfunction (allowing an X X X X analysis of causes, symptoms, recognition, and the effects on aircraft performance and handling) at the following points: (i) Prior to Vl decision speed; (ii) Between Vl and Vr (rotation speed); and (iii)Between Vr and 500 feet above ground level. 3.b.5. Flight control system failures, reconfiguration modes, manual X X X X reversion and associated handling. 3.b.6. Other 4. Climb. 4.a. Normal. X X X X 4.b. One or more engines inoperative. X X X X 4.c. Approach climb in icing (for airplanes with icing X X X X accountability). 4.d. Other 5. Cruise. 5.a. Performance characteristics (speed vs. power, confi2uration, and attitude) 5.a.l. Straight and level flight. X X X X 5.a.2. Change of airspeed. X X X X 5.a.3. High altitude handling. X X X X 5.a.4. High Mach number handling (Mach tuck, Mach buffet) and X X X X recovery (trim change).

5.a.5. Overspeed warning (in excess ofVmoor Mm0 ). X X X X 5.a.6. High lAS handling. X X X X 5.a.7. Other 5.b. Maneuvers 5.b.l. High Angle of Attack 5.b.l.a High angle of attack, approach to stalls, stall warning, and stall X X buffet (take-off, cruise, approach, and landing configuration) including reaction of the auto flight system and stall protection system. 5.b.l.b High angle of attack, approach to stalls, stall warning, stall X X buffet, and stall (take-off, cruise, approach, and landing

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

1-o t>~ Simulator Level ..... a Operations Tasks ~= = z A B c D configuration) including reaction of the auto flight system and stall protection system. 5.b.2. Slow flight X X 5.b.3. Upset prevention and recovery maneuvers within the FSTD's X X validation envelope. 5.b.4. Flight envelope protection (high angle of attack, bank limit, X X X X overspeed, etc.) 5.b.5. Turns with/without speedbrake/spoilers deployed X X X X 5.b.6. Normal and standard rate turns X X X X 5.b.7. Steep turns X X X X 5.b.8. Performance tum X X 5.b.9. In flight engine shutdown and restart (assisted and windmill) X X X X S.b.lO. Maneuvering with one or more engines inoperative, as X X X X appropriate S.b.ll. Specific flight characteristics (e.g. direct lift control) X X X X 5.b.12. Flight control system failures, reconfiguration modes, manual X X X X reversion and associated handling 5.b.l3 Gliding to a forced landing X X 5.b.14 Visual resolution and FSTD handling and performance for the following (where applicable by aircraft type and training program): 5.b.l4.a Terrain accuracy for forced landing area selection; X X 5.b.l4.b Terrain accuracy for VFR Navigation; X X 5.b.14.c Eights on pylons (visual resolution); X X 5.b.14.d Turns about a point; and X X 5.b.l4.e S-tums about a road or section line. X X 5.b.l5 Other. 6. Descent. 6.a. Normal X X X X 6.b. Maximum rate/emergency (clean and with speedbrake, etc.). X X X X 6.c. With autopilot. X X X X 6.d. Flight control system failures, reconfiguration modes, manual X X X X reversion and associated handling. 6.e. Other 7. Instrument Approaches And Landing. Those instrument approach and landing tests relevant to the simulated airplane type are selected from the following list. Some tests are made with limiting wind velocities, under windshear conditions, and with relevant system failures, including the failure of the Flight Director. If Standard Operating Procedures allow use autopilot for non- precision approaches, evaluation of the autopilot will be included. Level A simulators are not authorized to credit the landing maneuver. 7.a. Precision approach 7.a.l CAT I published approaches. 7.a.l.a Manual approach with/without flight director including X X X X

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

C']- Simulator Level -= a Operations Tasks ~i A B c D landing. 7.a.l.b Autopilot/autothrottle coupled approach and manual X X X X landing. 7.a.l.c Autopilot/autothrottle coupled approach, engine(s) X X X X inoperative. 7.a.l.d Manual approach, engine(s) inoperative. X X X X 7.a.l.e HUD/EFVS X X 7.a.2 CAT II published approaches. 7.a.2.a Autopilot/autothrottle coupled approach to DH and landing X X X X (manual and autoland). 7.a.2.b Autopilot/autothrottle coupled approach with one-engine- X X X X inoperative approach to DH and go-around (manual and autopilot). 7.a.2.c HUD/EFVS X X 7.a.3 CAT III published approaches. 7.a.3.a Autopilot/autothrottle coupled approach to landing and roll- X X X X out (if applicable) guidance (manual and auto land). 7.a.3.b Autopilot/autothrottle coupled approach to DH and go- X X X X around (manual and autopilot). 7.a.3.c Autopilot/autothrottle coupled approach to land and roll-out X X X X (if applicable) guidance with one engine inoperative (manual and autoland). 7.a.3.d Autopilot/autothrottle coupled approach to DH and go- X X X X around with one engine inoperative (manual and autopilot). 7.a.3.e HUD/EFVS X X 7.a.4 Autopilot/autothrottle coupled approach (to a landing or to a go- around): 7.a.4.a With generator failure; X X X X 7.a.4.b.l With maximum tail wind component certified or X X authorized; 7.a.4.b.2 With 10 knot tail wind; X X 7.a.4.c.l With maximum crosswind component demonstrated or X X authorized; and 7.a.4.c.2 With 10 knot crosswind. X X 7.a.5 PAR approach, all engine( s) operating and with one or more X X X X engine(s) inoperative 7.a.6 MLS, GBAS, all engine( s) operating and with one or more X X X X engine(s) inoperative 7.b. Non-precision approach. 7.b.l Surveillance radar approach, all engine(s) operating and with X X X X one or more engine(s) inoperative 7.b.2 NDB approach, all engine(s) operating and with one or more X X X X engine(s) inoperative

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

1-o ...c~ Simulator Level = e Operations Tasks ~ = z A B c D 7.b.3 VOR, VOR/DME, TACAN approach, all engines(s) operating X X X X and with one or more engine(s) inoperative 7.b.4 RNAV I RNP I GNSS (RNP at nominal and minimum X X X X authorized temperatures) approach, all engine(s) operating and with one or more engine(s) inoperative 7.b.5 ILS LLZ (LOC), LLZ back course (or LOC-BC) approach, all X X X X engine(s) operating and with one or more engine(s) inoperative 7.b.6 ILS offset localizer approach, all engine(s) operating and with X X X X one or more engine(s) inoperative 7.c Approach procedures with vertical guidance (APV), e.g. SBAS, fli2ht path vector 7.c.l APV/baro-VNAV approach, all engine(s) operating and with X X one or more engine(s) inoperative 7.c.2 Area navigation (RNAV) approach procedures based on SBAS, X X all engine(s) operating and with one or more engine(s) inoperative 8. Visual Approaches (Visual Segment) And Landings.

Flight simulators with visual systems, which permit completing a special approach procedure in accordance with applicable regulations, may be approved for that particular approach procedure.

8.a. Maneuvering, normal approach and landing, all engines X X X X operating with and without visual approach aid guidance 8.b. Approach and landing with one or more engines inoperative X X X X S.c. Operation of landing gear, flap/slats and speedbrakes (normal X X X X and abnormal) 8.d.l Approach and landing with crosswind (max. demonstrated) X X X X 8.d.2 Approach and landing with gusting crosswind X X 8.e. Approach and landing with flight control system failures, X X X X reconfiguration modes, manual reversion and associated handling (most significant degradation which is probable) 8.e.l. Approach and landing with trim malfunctions X X X X 8.e.l.a Longitudinal trim malfunction X X X X 8.e.l.b Lateral-directional trim malfunction X X X X 8.f. Approach and landing with standby (minimum) X X X X electrical/hydraulic power 8.g. Approach and landing from circling conditions (circling X X X X approach) 8.h. Approach and landing from visual traffic pattern X X X X 8.i. Approach and landing from non-precision approach X X X X 8.j. Approach and landing from precision approach X X X X 8.k. Other

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

... - Simulator Level ="~ e Operations Tasks ~ = z A B c D 9. Missed Approach. 9.a. All engines, manual and autopilot. X X X X 9.b. Engine(s) inoperative, manual and autopilot. X X X X 9.c. Rejected landing X X 9.d. With flight control system failures, reconfiguration modes, X X X X manual reversion and associated handling 9.e. Bounced landing recovery X X 10. Surface Operations (landing, after-landing and post-flight). lO.a Landing roll and taxi lO.a.l HUD/EFVS X X 10.a.2. Spoiler operation X X X X 10.a.3. Reverse thrust operation X X X X 10.a.4. Directional control and ground handling, both with and without X X X reverse thrust lO.a.S. Reduction of rudder effectiveness with increased reverse thrust X X X (rear pod-mounted engines) 10.a.6. Brake and anti-skid operation 10.a.6.a Brake and anti-skid operation with dry, patchy wet, wet on X X rubber residue, and patchy icy conditions 10.a.6.b Reserved 10.a.6.c Brake operation X X 10.a.6.d Auto-braking system operation X X X X 10.a.7 Other lO.b En2ine shutdown and parkin2 lO.b.l Engine and systems operation X X X X 10.b.2 Parking brake operation X X X X 10.b.3 Other 11. Any Fli2ht Phase. ll.a. Airplane and engine systems operation (where fitted) ll.a.l. Air conditioning and pressurization (ECS) X X X X ll.a.2. De-icing/anti-icing X X X X ll.a.3. Auxiliary power unit (APU). X X X X ll.a.4. Communications X X X X ll.a.S. Electrical X X X X ll.a.6. Fire and smoke detection and suppression X X X X ll.a.7. Flight controls (primary and secondary) X X X X ll.a.8. Fuel and oil X X X X ll.a.9. Hydraulic X X X X ll.a.lO. Pneumatic X X X X ll.a.ll. Landing gear X X X X ll.a.12. Oxygen X X X X ll.a.13. Engine X X X X

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Table A3A - Functions And Subjective Tests QPS REQUIREMENTS

... - Simulator Level ="~ e Operations Tasks ~ = z A B c D 11.a.14. Airborne radar X X X X 11.a.15. Autopilot and Flight Director X X X X 11.a.16. Terrain awareness warning systems and collision avoidance X X X X systems (e.g. EGPWS, GPWS, TCAS) 11.a.17. Flight control computers including stability and control X X X X augmentation 11.a.18. Flight display systems X X X X 11.a.19. Flight management computers X X X X 11.a.20. Head-up displays (including EFVS, if appropriate) X X X X 11.a.21. Navigation systems X X X X 11.a.22. Stall warning/avoidance X X X X 11.a.23. Wind shear avoidance/recovery guidance equipment X X X X 11.a.24. Flight envelope protections X X X X 11.a.25. Electronic flight bag X X 11.a.26. Automatic checklists (normal, abnormal and emergency X X procedures) 11.a.27. Runway alerting and advisory system X X 11.a.28. Other 11.b. Airborne procedures 11.b.1. Holding X X X X 11.b.2. Air hazard avoidance (traffic, weather, including visual X X correlation) 11.b.3. Windshear 11.b.3.a Prior to take-off rotation X X 11.b.3.b At lift-off X X 11.b.3.c During initial climb X X 11.b.3.d On final approach, below 150m (500ft) AGL X X 11.b.4. Effects of airframe ice X X

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS For Qualification At The Stated Level C>~"" Simulator Level -= a ~ = Class I Airport Models z A B c D This table specifies the minimum airport model content and functionality to qualify a simulator at the indicated level. This table applies only to the airport models required for simulator qualification; i.e., one airport model for Level A and Level B simulators; three airport models for Level C and Level D simulators. Begin QPS Requirements 1. Functional test content requirements for Level A and Level B simulators. The following is the minimum airport model content requirement to satisfy visual capability tests, and provides suitable visual cues to allow completion of all functions and subjective tests described in this attachment for simulators at Levels A and B. l.a. A minimum of one ( 1) representative airport model. This model X X identification must be acceptable to the sponsor's TPAA, selectable from the lOS, and listed on the SOQ. l.b. The fidelity of the airport model must be sufficient for the X X aircrew to visually identify the airport; determine the position of the simulated airplane within a night visual scene; successfully accomplish take-offs, approaches, and landings; and maneuver around the airport on the ground as necessary. l.c. Runways: X X l.c.l. Visible runway number. X X l.c.2. Runway threshold elevations and locations must be modeled to X X provide sufficient correlation with airplane systems (e.g., altimeter). l.c.3. Runway surface and markings. X X l.c.4. Lighting for the runway in use including runway edge and X X centerline. l.c.S. Lighting, visual approach aid and approach lighting of X X appropriate colors. l.c.6. Representative taxiway lights. X X 2.a. Additional functional test content requirements 2.a.1 Airport scenes 2.a.l.a A minimum of three (3) real-world airport models to be X X consistent with published data used for airplane operations and capable of demonstrating all the visual system features below. Each model should be in a different visual scene to permit assessment ofFSTD automatic visual scene changes. The model identifications must be acceptable to the sponsor's TPAA, selectable from the IOS, and listed on the SOQ. 2.a.l.b Reserved 2.a.l.c Reserved 2.a.l.d Airport model content. X X X X For circling approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing. If all runways in an airport model used to meet the requirements of this

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS "" For Qualification At The Stated Level C>~ Simulator Level -= a ~ = Class I Airport Models z A B c D attachment are not designated as "in use," then the "in use" runways must be listed on the SOQ (e.g., KORD, Rwys 9R, 14L, 22R). Models of airports with more than one runway must have all significant runways not "in-use" visually depicted for airport and runway recognition purposes. The use of white or off white light strings that identify the runway threshold, edges, and ends for twilight and night scenes are acceptable for this requirement. Rectangular surface depictions are acceptable for daylight scenes. A visual system's capabilities must be balanced between providing airport models with an accurate representation of the airport and a realistic representation of the surrounding environment. Airport model detail must be developed using airport pictures, construction drawings and maps, or other similar data, or developed in accordance with published regulatory material; however, this does not require that such models contain details that are beyond the design capability of the currently qualified visual system. Only one "primary" taxi route from parking to the runway end will be required for each "in-use" runway. 2.a.2 Visual scene fidelity. 2.a.2.a The visual scene must correctly represent the parts of the airport X X X X and its surroundings used in the training program. 2.a.2.b Reserved 2.a.2.c Reserved 2.a.3 Runways and taxiways. 2.a.3.a Airport specific runways and taxiways. X X X X 2.a.3.b Reserved 2.a.3.c Reserved 2.a.4 If appropriate to the airport, two parallel runways and one X X crossing runway displayed simultaneously; at least two runways must be capable of being lit simultaneously. 2.a.5 Runway threshold elevations and locations must be modeled to X X provide correlation with airplane systems (e.g. HUD, GPS, compass, altimeter). 2.a.6 Slopes in runways, taxiways, and ramp areas must not cause X X distracting or unrealistic effects, including pilot eye-point height variation. 2.a.7 Runway surface and markings for each "in-use" runway must include the following, if appropriate: 2.a.7.a Threshold markings. X X X X 2.a.7.b Runway numbers. X X X X 2.a.7.c Touchdown zone markings. X X X X 2.a.7.d Fixed distance markings. X X X X

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS

For Qualification At The Stated Level ...... ~~ -a Simulator Level ~i= Class I Airport Models A B c D 2.a.7.e Edge markings. X X X X 2.a.7.f Center line markings. X X X X 2.a.7.2 Distance remaining signs. X X X X 2.a.7.h Signs at intersecting runways and taxiways. X X X X 2.a.7.i Windsock that gives appropriate wind cues. X X 2.a.8 Runway lighting of appropriate colors, directionality, behavior and spacing for the "in-use" runway includin2 the followin2: 2.a.8.a Threshold lights. X X X X 2.a.8.b Edge lights. X X X X 2.a.8.c End lights. X X X X 2.a.8.d Center line lights. X X X X 2.a.8.e Touchdown zone lights. X X X X 2.a.8.f Lead-off lights. X X X X 2.a.8.2 Appropriate visual landing aid(s) for that runway. X X X X 2.a.8.h Appropriate approach lighting system for that runway. X X X X 2.a.9 Taxiway surface and markine;s (associated with each "in-use" runway): 2.a.9.a Edge markings X X X X 2.a.9.b Center line markings. X X X X 2.a.9.c Runway holding position markings. X X X X 2.a.9.d ILS critical area markings. X X X X 2.a.9.e All taxiway markings, lighting, and signage to taxi, as a X minimum, from a designated parking position to a designated runway and return, after landing on the designated runway, to a designated parking position; a low visibility taxi route (e.g. surface movement guidance control system, follow-me truck, daylight taxi lights) must also be demonstrated at one airport model for those operations authorized in low visibilities. The designated runway and taxi routing must be consistent with that airport for operations in low visibilities.

The qualification of surface movement guidance control systems (SMGCS) is optional at the request of the FSTD sponsor. For the qualification of SMGCS, a demonstration model must be provided for evaluation. 2.a.10 Taxiway lighting of appropriate colors, directionality, behavior and spacing (associated with each "in-use" runway): 2.a.10.a Edge lights. X X X X 2.a.10.b Center line lights. X X X X 2.a.10.c Runway holding position and ILS critical area lights. X X X X 2.a.11 Required visual model correlation with other aspects of the airport environment simulation. 2.a.11.a The airport model must be properly aligned with the navigational X X X X aids that are associated with operations at the runway "in-use".

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS

1-o For Qualification At The Stated Level ...... C>~ a Simulator Level ~= = Class I Airport Models z A B c D 2.a.11.b The simulation of runway contaminants must be correlated with X the displayed runway surface and lighting. 2.a.12 Airport buildin2s, structures and li2htin2. 2.a.12.a Buildings, structures and lighting: 2.a.12.a.l Airport specific buildings, structures and lighting. X X 2.a.12.a.2 Reserved 2.a.12.a.3 Reserved 2.a.12.b At least one useable gate, set at the appropriate height (required X X only for those airplanes that typically operate from terminal gates). 2.a.12.c Representative moving and static airport clutter (e.g. other X X airplanes, power carts, tugs, fuel trucks, additional gates). 2.a.12.d Gate/apron markings (e.g. hazard markings, lead-in lines, gate X X numbering), lighting and gate docking aids or a marshaller. 2.a.13 Terrain and obstacles. 2.a.13.a Terrain and obstacles within 46 km (25 NM) of the reference X X airport. 2.a.13.b Reserved 2.a.14 Si2nificant, identifiable natural and cultural features and movin2 airborne traffic. 2.a.14.a Significant, identifiable natural and cultural features within 46 X X km (25 NM) of the reference airport. Note.- This refers to natural and cultural features that are typically used for pilot orientation in flight. Outlying airports not intendedfor landing need only provide a reasonable facsimile of runway orientation. 2.a.14.b Reserved 2.a.14.c Representative moving airborne traffic (including the capability X X to present air hazards - e.g. airborne traffic on a possible collision course). ~.b Visual scene mana2ement. 2.b.l All airport runway, approach and taxiway lighting and cultural X X lighting intensity for any approach must be capable of being set to six (6) different intensities (0 to 5); all visual scene light points should fade into view appropriately. 2.b.2 Airport runway, approach and taxiway lighting and cultural X X lighting intensity for any approach must be set at an intensity representative of that used in training for the visibility set; all visual scene light points should fade into view appropriately. 2.b.3 The directionality of strobe lights, approach lights, runway edge X X X X lights, visual landing aids, runway center line lights, threshold lights, and touchdown zone lights on the runway of intended landing must be realistically replicated. ~.c Visual feature reco2nition.

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS

For Qualification At The Stated Level C>]- Simulator Level -= a ~ = Class I Airport Models z A B c D Note.- The following are the minimum distances at which runway features should be visible. Distances are measured from runway threshold to an airplane aligned with the runway on an extended 3-degree glide slope in suitable simulated meteorological conditions. For circling approaches, all tests below apply both to the runway usedfor the initial approach and to the runway of intended landing. 2.c.l Runway definition, strobe lights, approach lights, and runway X X X X edge white lights from 8 km (5 sm) of the runway threshold. 2.c.2 Visual approach aids lights. 2.c.2.a Visual approach aids lights from 8 km (5 sm) of the runway X X threshold. 2.c.2.b Visual approach aids lights from 4.8 km (3 sm) of the runway X X threshold. 2.c.3 Runway center line lights and taxiway definition from 4.8 km X X X X (3 sm). 2.c.4 Threshold lights and touchdown zone lights from 3.2 km (2 sm). X X X X 2.c.5 Runway markings within range of landing lights for night scenes; X X X X as required by the surface resolution test on day scenes. 2.c.6 For circling approaches, the runway of intended landing and X X X X associated lighting must fade into view in a non-distracting manner. ~.d Selectable airport visual scene capability for: 2.d.l Night. X X X X 2.d.2 Twilight. X X 2.d.3 Day. X X 2.d.4 Dynamic effects - the capability to present multiple ground and X X air hazards such as another airplane crossing the active runway or converging airborne traffic; hazards should be selectable via controls at the instructor station. 2.d.5 Illusions - operational visual scenes which portray X representative physical relationships known to cause landing illusions, for example short runways, landing approaches over water, uphill or downhill runways, rising terrain on the approach path and unique topographic features. Note.- Illusions may be demonstrated at a generic airport or at a specific airport. ~.e Correlation with airplane and associated equipment. 2.e.l Visual cues to relate to actual airplane responses. X X X X 2.e.2 Visual cues durin2 take-off, approach and landin2. 2.e.2.a Visual cues to assess sink rate and depth perception during X X X landings. 2.e.2.b Visual cueing sufficient to support changes in approach path by X X X X using runway perspective. Changes in visual cues during take-off, approach and landing should not distract the pilot.

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS For Qualification At The Stated Level C>~"" Simulator Level -= a ~ = Class I Airport Models z A B c D 2.e.3 Accurate portrayal of environment relating to airplane attitudes. X X X X 2.e.4 The visual scene must correlate with integrated airplane systems, X X where fitted (e.g. terrain, traffic and weather avoidance systems and HUD/EFVS). 2.e.5 The effect of rain removal devices must be provided. X X 2.f Scene quality. 2.f.l Quantization. 2.f.l.a Surfaces and textural cues must be free from apparent X X quantization (aliasing). 2.f.l.b Surfaces and textural cues must not create distracting X X quantization (aliasing). 2.f.2 System capable of portraying full color realistic textural cues. X X 2.f.3 The system light points must be free from distracting jitter, X X X X smearing or streaking. 2.f.4 System capable of providing representative focus effects that X X simulate rain (e.g. reduced visibility and object resolution in the out the window view as a result of rain). 2.f.5 System capable of providing light point perspective growth (e.g. X X relative size of runway and taxiway edge lights increase as the lights are approached). 2.g Environmental effects. 2.g.l The displayed scene must correspond to the appropriate surface X X contaminants and include runway lighting reflections for wet, partially obscured lights for snow, or suitable alternative effects. 2.g.2 Special weather representations which include the sound, motion X X and visual effects of light, medium and heavy precipitation near a thunderstorm on take-off, approach and landings at and below an altitude of 600 m (2 000 ft) above the airport surface and within a radius of 16 km (10 sm) from the airport. 2.g.3 One airport with a snow scene to include terrain snow and snow- X X covered taxiways and runways. 2.g.4 In-cloud effects such as variable cloud density, speed cues and X X ambient changes should be provided. 2.g.5 The effect of multiple cloud layers representing few, scattered, X X broken and overcast conditions giving partial or complete obstruction of the ground scene. 2.g.6 Gradual break-out to ambient visibility/RVR, defmed as up to X X 10% of the respective cloud base or top, 20 ft ~ transition layer ~ 200 ft; cloud effects should be checked at and below a height of 600 m (2 000 ft) above the airport and within a radius of 16 km (1 0 sm) from the airport. Transition effects should be complete when the IOS cloud base or top is reached when exiting and start when entering the cloud, i.e. transition effects should occur

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Table A3B - Functions and Subjective Tests QPS REQUIREMENTS

For Qualification At The Stated Level .....t'] - Simulator Level ~= = Class I Airport Models z A B c D within the IOS defined cloud layer. 2.g.7 Visibility and RVR measured in terms of distance. X X X X Visibility/RVR must be checked at and below a height of 600 m (2 000 ft) above the airport and within a radius of 16 km (10 sm) from the airport. 2.g.8 Patchy fog (sometimes referred to as patchy RVR) giving the X X effect of variable RVR. The lowest RVR should be that selected on the IOS, ie. variability is only greater than the IOS RVR. 2.2.9 Effects of fog on airport lighting such as halos and defocus. X X 2.g.10 Effect of ownship lighting in reduced visibility, such as reflected X X glare, to include landing lights, strobes, and beacons. 2.g.ll Wind cues to provide the effect of blowing snow or sand across a X X dry runway or taxiway should be selectable from the instructor station. End QPS Requirement -- Be2in Information 3. An example of being able to "combine two airport models to achieve two "in-use" runways: One runway designated as the "in use" runway in the frrst model of the airport, and the second runway designated as the "in use" runway in the second model of the same airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right. Two airport visual models might be used: the first with Runway 27 designated as the "in use" runway for the approach to runway 27, and the second with Runway 18 Right designated as the "in use" runway. When the pilot breaks off the ILS approach to runway 27, the instructor may change to the second airport visual model in which runway 18 Right is designated as the "in use" runway, and the pilot would make a visual approach and landing. This process is acceptable to the FAA as long as the temporary interruption due to the visual model change is not distracting to the pilot, does not cause changes in navigational radio frequencies, and does not cause undue instructor/evaluator time. 4. Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within the capabilities of the system. End Information

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* * * * * ■ 3. Correct the tables appearing on pages 18308–18326 to read as follows:

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■ 4. On page 18327, correct amendatory ■ 15. Amend Attachment 2 to Appendix ■ A. Revise paragraph 2.e; instruction 15 to read as follows: B as follows: ■ B. Revise Table B2A;

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■ C. Revise Table B2B; The revisions and additions read as ■ 5. Correct the tables appearing on ■ D. Revise Table B2C; follows: pages 18329–18375 to read as follows: ■ E. Revise Table B2D; and * * * * * ■ F. Revise Table B2E.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00102 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.098 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32117 gear icing applied. in de-ice configured be normally, accordance flap. performance be and in Notes should approach accountability should airplane operating an anti-ice go-around all the for icing and INFORMATION considerations, data conditions, systems up with with Airplane All 7 X X X X X X FTD Level 5 6 of or of 3 range, range, two least interval interval rating weight manual manual descent icing Tests at of an an of of minimum in minimum segment. of speed speed a a thrust showing ft) over over 80% 80% landing normal to to at spread minimum a a approach performance performance (5,000 airspeed operating operating airspeed snapshot Ob_jective or ft). recorded recorded an m continuous with reduced reduced Test descent be be certificated small small Details be be a a flow, to to single change. airplane airplane flight. 1,550 increase decrease (1,000 power. a a or or to to m (FTD) fuel may may with with be altitude. used. used. snapshots maximum idle speed speed change. stabilized steady least data data applicable to 300 maximum be be mid may in at be test test at using using required required performance performance least near for may may power test airplanes airplanes Device kt, kt, may at instantaneous conditions. data consecutive data as 50 50 speed change speed speed change minutes For FTD FTD Flight For Flight Idle Test Time Time The Test operational operational equivalent. of Training Flight Flight Conditions REQUIREMENTS Cruise Cruise Cruise. Clean Clean. Approach B2A- QPS or Nl Table min) fuel climb, descent. ftl ±3% flow. of of ±10% than or (100 (200ft/min) ±10% performance rate rate oftorque. fuel less time, airspeed. airspeed. of of m/s m/s EPR Tolerance not kt kt ±5% ±5% data. distance, airplane but used or or ±0.5 ±1.0 ±.05 ±3 ±10% ±5%Time ±5% ±5% ±3 ±5%Time of route if phase the Approach En airplanes in Descent. performance this I Title performance. for flight flight icing for Engine Engine descent. Test data deceleration. airplane accountability Cruise acceleration provided Level Level Inoperative Idle Inoperative Climb flight. Climb. Cruise One One with Entry Number l.c.3. l.d.2. l.d.3. l.d.4. l.c.4. l.d. l.d.l.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00104 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.100 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32119 for for part part . 1 T T,. this this and and of of F F Notes ofTi. ofTi, both Appendix Appendix the could INFORMATION for definitions definitions See See .fixtures equipment used 7 test X be conducting 6 could instrumentation measurinf( FTD while Level external 5 X X X X X X of this lieu external from in test test equipment go- the the FTD. to data usinf( take-off in in instrumentation flight flight Tests the by method the in contaminated acceptable contaminated acceptable power performance measuring available. change change of of position an an runway runway idle maximum are are and MQTG, dry dry where alternative hardware effects effects external from from the on on Objective An force in instrumentation the the Test incremental incremental used, Details manufacturer's using The the based based be and and the the airplane or by coefficients, coefficients, of is is control. parameter parameter of (FTD) power. included data, data, FTD. must test the is use idle the distance distance at verified braking braking data by engine engine power. to flight response response into Verification Device was solely critical critical alternative. alternative. around stopping stopping power manual runway runway Engineering Either Engineering Total Total built comparison measured checks. be generated Training should control instrumentation are satisfactory landing the time instrumentation the or Flight or of Flight forces required - if Conditions REQUIREMENTS all force Provided of measuring Landing. Ground Approach B2A evidence QPS data. versus and applicable that s s and and not s. s. s. s. s; s; ±1 ±1 Table and ±10% is or airplane measurement position recording FTD: FTD: FTD: FTD: FTD: FTD: ±0.2S ±0.2S ±0.2S ±0.2S ±0.2S ±0.2S the the force means, 7 7 6 6 or or or or or or to have for (200ft) Ti Ti Tt Tt Tt Tt to Tolerance controller m Level Level Level LevelS LevelS Level versus distance. be For For For For For matched For of ±10% ±10% ±10% ±10% ±10% ±10% ±61 yaw equivalent or evaluations would and and position of roll Tests. icy checks, controls recorded recurrent Testing Pitch, distance, Title - Control and brakes, control flight 2- directly the Test Qualities. be initial Static Stopping runway. runway. Deceleration. Engines. at Note Note.] static wheel Acceleration. Handling Entry Number l.e.4. l.f. l.f.2. l.f.l. 2.a. 2.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00105 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.101 32120 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations such such The The to to steady tests tests other other validated validated control control able able compare compare the static or or continuing continuing be be trims, from from be be to to the the on on on instrument instrument to to etc. test test etc. not not 5 5 data data evaluations. evaluations. an an Notes should should only only design design and and fly fly flight flight stalls, to to longitudinal engine-out Level Level to to a is is side-slips, as as in-flight in-flight results results for for time INFORMATION interconnected the FTD, intent intent qualification qualification data. approach; approach; stability, such such state manually manually results results Test Test feel feel with with Applicable Applicable any as the 7 in without 6 X X X X mechanically pressures FTD used Level not 5 X X be are impact interconnected or could to to sweep sweep feel controls to to Tests of sweep sweep same control control apply apply installation mechanically sets the control control at are both qualification qualification continuing continuing if on on Objective tolerances tolerances permanent controls initial initial Test a uninterrupted uninterrupted If Details required an an uninterrupted uninterrupted accomplished Such recorded recorded during during for for an an (FTD) be sides. only evaluations. evaluations. comparisons comparisons is for for The The both system. results results results results should to stops. stops. Device stops. stops. controls the the tests loading qualification qualification subsequent subsequent Record Record Record Record evaluation evaluation the the to to pilot applicable of control is control set Training the data flight by by to of second set Flight the made Flight dynamic - Conditions are REQUIREMENTS determined determined single from and a sponsor sponsor Ground. Ground. As As if B2A QPS repairs Static testing Table provider and/or or or or or control devices. data angle. lbt) lbt) lbt) lbt) lbt) lbt) lbt) lbt) angle. angle. ( 5 ( ( 5 ( (2 (2 (2 (2 (3 (3 the force. force. force. force. external of of of of daN daN daN daN daN daN daN daN Tolerance FTD static of elevator aileron spoiler from modifications o 1.3 1.3 breakout. breakout. breakout. breakout. ±2.2 ± ±2.2 ±3 ±2° ±2° ±0.9 ±0.9 ±0.9 ±0.9 ± ±10% ±10% ±10% ±10% only) applicable. major required sufficient. if FTD is installation is 7 where force force force force the tests position position data repeated (Level for of versus versus versus versus rationale Title be set lost A controller controller 3- controller controller surface surface Test being calibration. calibration. and and position position position position Pitch Pitch Roll Roll validation Note FTD. should single Entry Number 2.a.l.a. 2.a.l.b. 2.a.2.a. 2.a.2.b.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00106 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.102 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32121 such flight The to value. to steady tests position is other validated control able compare FSTD or continuing be test trims, from be to the the on instrument to etc. surface the test computed not 5 data evaluations. an of Notes should only design and fly flight against FSTD model to engine-out Level to is side-slips, as in-flight results purpose for INFORMATION intent qualification compare indicator data. data. controls approach; state such results manually Test The feel with Applicable 7 X X X X X X X X X FTD Level 5 6 X to to to to sweep sweep sweep sweep to induced Tests sweep control apply control control control primary control qualification continuing pilot on Ob_jective tolerances at initial Test uninterrupted uninterrupted uninterrupted uninterrupted Details an an an an uninterrupted checked recorded during of of of for an (FTD) evaluations. be comparisons for The to results results results results results stops. rate Device stops. stops. stops. stops. the qualification subsequent Record Record Record Record Record Trim evaluation the the the to the Training by approach. Flight and Flight Conditions REQUIREMENTS determined sponsor Ground. Ground Ground. Ground. Ground. Ground. As B2A- QPS /s) 0 ( Table or or or or rate lbt) lbt) lbt) lbt) lbt) lbt) lbt) lbt) angle. angle. (3 (3 ( 5 ( (2 ( 5 ( (2 ( 5 ( ( 5 ( trim force. force. force. force. of of of of of trim daN daN daN daN daN daN daN daN Tolerance rudder 1.3 1.3 breakout. breakout. breakout. breakout. ±0.5° ±2° ± ± ±10% ±10% ±10% ±2°NWA. ±10% ±2°NWA. ±10% ±2.2 ±0.9 ±2.2 ±0.9 ±2.2 ±2.2 and force force position Rate. Steering Steering Position Indicator Force Force Calibration. Calibration. versus versus pedal pedal Pedal Title Trim Trim surface Surface Test Pitch calibration. and Steering position position Position Pitch Rudder Rudder Rudder Controller Controller Calibration. vs. Nosewheel Nosewheel Entry Number 2.a.6. 2.a.7. 2.a.4.b. 2.a.3.b. 2.a.S. 2.a.4.a. 2.a.3.a.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00108 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.104 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32123 a for 2 of an Figure critically of for 4 A period reference see and the Attachment Notes of information. A, paragraph systems, Appendix sequential to of oscillation. overdamped the INFORMATION = illustration damped additional n measurement. For Refer full A2B Appendix 7 X 6 FTD Level 5 in of of See of the Tests 50% values deflection to 50% maneuvering within to displacements specified. the 25% absolute by 25% controller the control Ob.iective independently). generated Test otherwise pitch limited Details against normal (approximately unless (FTD) for approximately (considered completely apply allowable be or conditions flight are must period directions envelope). throw Device level flight forces both maximum Data Tolerances load full for each for control required Trainine the and that be where Cruise, Flieht Flight may - FTDs Conditions REQUIREMENTS for Landing. Takeoff, setting B2A QPS of of Power ofPn applicable or or or Table largest control band. 1 ±0.5% 2 0 travel Amax, 2. 1)% not A.!= FTD. the or ±0.5% overshoot). of position ofP ofP ofP is of (minimum the or are s. control band residual in stop). state Amax s. s. s. maximum ±10% ±5% = ±10*(n+ ±10% ±20% ±30% to Tolerance 2.b.3 underdamped ) ) 1 2 total significant Attachment ±0.05 the significant and A, 1 amplitude (stop systems: Steady residual T(P For T(P T(Po) T(An) T(Pn) or overshoots T(A.i) of ±0.05 ±0.05 ±I ±0.05 where the travel installed 2.b.2 unit Tests. Appendix 2.b.l, of 4 Control controller Tests Title Control. Test Dynamic Pitch airplane Note.- paragraph Entry Number 2.b. 2.b.l.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00110 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.106 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32125 an Figure critically for A reference see and the Notes of systems, Appendix of overdamped INFORMATION illustration damped measurement. For A2B 7 X X 6 FTD Level 5 state. at at before a the rate). ILS ILS rate). be exhibit 5 s until to until Tests directions. an an control control both of roll pitch on on that must both input. input. minor minor before before 2°/S 2°/S in direction. reversal of of to to 5 s 5 s there test minimum control control non-normal non-normal airplanes 0.5 0.5 a demonstrate Ob_jective established established from from control of of typical typical opposite be to to and and Test For be be Details data data the directions, while while behavior, used used must before to must must is is (FTD) normal normal initiation initiation 5 s both directions. direction. made made in in history history there test test of (approximately (approximately direction. after after inputs inputs reversal one both s s Test Test time time 5 5 in in single single Device a a control corrections demonstrate directions, corrections approach approach CCA: CCA: Show Show minimum non-symmetrical If If Control Test least opposite Control Test least Training landing. or or Landing. Flight Flight Conditions REQUIREMENTS Approach Approach B2A- QPS or rate roll rate Table body time pitch body roll throughout peak the applied of peak body body history. of rate Tolerance applied time ±20% pitch rate history. or ±0.15°/s ±0.15°/s ±20% the throughout Inputs Inputs Title Control Control Test Small Small -Pitch. -Roll. Entry Number 2.b.4. 2.b.5.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00114 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.110 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32129 at . typically testing conducted stall airplane Notes be gravity for of may INFORMATION certification centers required Tests 7 X FTD Level 5 6 X X at be do 25° but mode, system first must thrust Record if (required least required objective this task, second which the Tests conducted at conditions of as control tolerance. with and Part. stability, be settings. The (lg). three buffet of vibration a this the flap condition buffet airplanes must level (!g) of stall) of entered initial flight to with entry methods entry A characteristics. numerical stall subjective be non-normal Ob_jective one qualification level aircraft) and wings stall the or Test different positive static configuration. for power-on condition applies Details must approach/landing at turning least and a exhibit stability equipped signal wings with at (accelerated Appendix in in and stall, at applicable (FTD) be normal in in exhibit that cruise a turboprop (clean) following power method in speed the of angle for entry entry maneuver comply entry must climb conducted warning the must idle Test 5 FTD. conditions: of be not only bank stall required meets flaps-up airplanes Stall Stall Stall Device exhibit stall FTD applicable. near a the . . . indication in in demonstrated CCA: as applicable. segment must requirements not need For Level Each The The or flight Alternative the the that and Training Climb, Climb, or Cruise or Landing Flight Condition), Segment Segment Flight Performance Altitude Conditions Approach REQUIREMENTS and (Near Second Second High Landing. Limited Approach B2A- QPS of or be initial Table break" those control (2.2 must attack for "g angle for device and speeds lb actuation of to demonstrate angle angle with flight for ±5 speeds. inputs and trend than airspeed, stall warning, or Stick/Column buffet. angle sideslip pitch bank airspeed (prior Tolerance stall bank kts. kt initial daN)) correct and simulators stall warning systems: plotted buffet, magnitude. reversible only). force greater Control ±2.0° ±3 ±2.0° ±2.0° ±2.0° ±3 ±10% ±2° Additionally, device.) (actuation Stall to Title Warning Test stall warning Approach characteristics of Stall Entry Number 2.c.8.b. 2.c.8.a.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00115 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.111 32130 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations in mel v defined or be control mea v manner. may of Notes prevents speed which performance or conventional a INFORMATION demonstration by Minimum limit the 7 X X X X X FTD Level 5 6 X X X X after state, mode. double the cycles non- or control of Tests roll of used. damping. that and control less half be control or mode. mode. operating overshoots is one number may the normal displacement (six to maximum cycles in the Non-normal control control on of data non-normal less. Ob_jective or full time set representative non-normal and is cycles whichever Test or Test control be in Details three roll snapshot FTD) one-third mode. Test must (FTD) non-normal non-normal Normal normal include 7 or determine determine in in in completed), in Three full whichever include travel). to to normal is FTD) must thrust control 6 Test Test Test (Level Test history with must test Device input applicable. controller as CCA: CCA: amplitude, CCA: CCA: CCA: (Level (approximately states. sufficient necessary normal Time Test Takeoff Test The engine(s). following: the or Training most airplane). Approach is Landing the specified. Flight or Flight and in Conditions REQUIREMENTS critical (whichever Landing. Takeoff Cruise, Cruise. Cruise. Cruise. B2A- otherwise QPS half or unless ratio. Table roll or one of to flight angle rate. amplitude period. damping ±10% level normal oftime of period, of pitch or pitch airspeed. g Tolerance for kt double 0% 0% damping. acceleration rate. Representative or ±2°/s ±1.5° ±10% ±I ±I ±2°/s ±0.1 ±3 ±0.02 Tests. required the or that low per in is mea) or handling mel), control (V Dynamics. Dynamics. Directional (V Title air setting engine- Period Response Test inoperative characteristics air. applicable airworthiness (Reserved) (Rate). speed speed, Short requirement Roll Phugoid Power Dynamics. Phugoid Minimum Lateral landing Entry Number 2.d.2. 2.c.10 2.c.9.b. 2.d. 2.c.9.a. 2.d.1. 2.c.ll.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00116 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.112 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32131 the to the step of and a seconds 20° 0 When return I apply using neutral response. one-third travel. to abruptly Notes level, input free approximately bank, approximately wings controller controller of control airplane INFORMATION allow approximately roll reaching roll With roll of 30° 7 X 6 X X X FTD Level 5 X may may may of mode. non- roll roll Tests a a tests tests tests input and response control control control mode. mode. with with step roll 2.d.3. tum tum normal multiple multiple multiple lateral lateral with with in control control test Ob.iective from from from 30°. 30°. non-normal steady steady show show Test Test a a in Details test, test, combined combined FTD) controller mode. Test (FTD) non-normal non-normal averaged averaged averaged be be 7 directions. directions. in in maintain maintain roll 2.d.2. data data data may may FTD) to to approximately approximately both both control 6 Test Test (Level alternative alternative deck of of test test test for for Device an an used. used. angle CCA: CCA: CCA: angle (Level (rate) be be normal required required Test Test This This flight As Airplane Airplane Airplane As or Trainine Approach or Landing. Flieht Flight and - Conditions REQUIREMENTS Landing. Cruise Cruise, Cruise Approach B2A QPS or or 20 20 o in in ±2° ±3 Table used: ±2° FTD or control roll force. is 7 and and with of angle angle and lbt) test flight (3 roll roll wheel (Level trend trend trend angle. trend ±10% of of of daN Tolerance or airplanes alternate 1.3 aileron correct angle. s. s. systems reversible For If Correct Correct Correct only): ±2° ±10% ±10% ±10% ± flight of controller. Title Stability. Stability. Stability. roll input Test deck Step Spiral Spiral Spiral Entry Number 2.d.3. 2.d.4.a. 2.d.4.b. 2.d.4.c.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00120 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.116 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32135 Notes INFORMATION theNSPM. 7 X 6 FTD Level 5 a a ft) to for (33 runway. airplane Tests headwind AGL of the 10m as profile, touchdown to at 60% (200ft) gear wind m least provided respect at Ob_jective be measured of landing of61 Test with including Details must value main data, values (FTD) in minimum component test runway. a components decrease from crosswind Device requires above the crosswind performance data It 50% Test and speed. Wind Training Flight Flight Conditions REQUIREMENTS Landing. B2A- QPS of of Table or or or control pedal force. ±10% ±10% with angle. angle. or or lbt) lbt) angle. flight (Slbt) (3 ( 5 ( rudder wheel angle. force. of of pitch airspeed. (10ft) (10ft) daN daN daN Tolerance side-slip roll heading airplanes kt 1.3 10% column systems: height. height. reversible For force. ±3 ±1.5° ±1.5° AOA. ±1.5° AOA. ±10%of ±10% ± ±2.2 ± ±2° ±2° ±3m ±3m ±3° ±2.2 Landing. Title Engine Test Inoperative One Entry Number 2.e.4.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00121 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.117 32136 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations for part this of F Notes ofTr. Appendix INFORMATION definition See 7 X X X X 6 FTD Level 5 and be non- using speed. in main weight. Tests record near must 50% with and thrust a applicable) to directions full (if medium conducted weight required touchdown engage guidance, speed. at both go-around be in gear to noted. Objective reaching mode landing touchdown be Test autopilot test roll-out input Details go-around operating autopilot until flare landing applicable) from with must inoperative. (FTD) (if pedal test autopilot. thrust provides main certificated in minimum autopilot one all-engine inoperative mode. engine deviation rudder Non-autopilot of touchdown without reverse Device autopilot decrease demonstrated critical CCA: normal maximum reverser Provide Engine gear lateral If Time one full Apply Normal Training Flight Flight airplane airplane - Conditions REQUIREMENTS per per performance data. performance data. Landing. Landing. As As B2A QPS Table roll- ofTf. at ftlmin) flare angle. angle. angle. lateral angle. angle. 10% rate. ft) during (140 angle. angle. (5 descent or± pitch pitch yaw airspeed. airspeed. airspeed. (10ft) AOA. s m/s m Tolerance of side-slip side-slip roll heading roll kt kt kt deviation rate height. out. ±0.5 ±3 ±2° ±0.7 ±2° ±1.5° AOA. ±1.5° ±2° ±3° ±1.5 ±5 ±2° ±3 ±1.5° ±3m ±2°/s touchdown. ±1.5° (if control go autopilot landing effectiveness) Title symmetric engine Test inoperative applicable). around. (rudder Directional go-around. One Autopilot All-engine with Entry Number 2.e.7. 2.e.5. 2.e.8. 2.e.6.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00122 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.118 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32137 Effect additional for Ground on Notes attachment paragraph INFORMATION this information. in See 7 X X X X X X X X FTD Level 5 6 of thrust or jUnction pedal response Tests of reached. control their is input justification if rudder results operating with speed pedal with states the non-normal Objective on history or Test rudder provided heading Details control operation Time thrust be (FTD) normal in must maximum maintain reverse applicable. degraded minimum Test as airplanes. until full and Device rationale input CCA: reverser mode, results. With engine(s), A fUnction. normal with Training Climb, and (i.e. computer-controlled to or Landing. Cruise, Cruise. Flight Segment Flight Approach. envelope protection envelope - Conditions REQUIREMENTS the Second Landing. Landing. Takeoff, applicable Takeoff, Cruise, Cruise. Approach Approach. B2A reach QPS protectionfonction only to Functions. are factor angle or Table ±10% angle. 2.h envelope attack load required or bank of angle. angle. of thrust angle as ft) angle. each 0% Protection net (5 ±1 stabilizer normal angle pitch airspeed. airspeed. airspeed. airspeed. of m Tolerance into thrust elevator pitch heading AOA. or kt kt kt kt height. o o Set of equivalent. ± 1 ± ±3 ±5% ± 1 ± ±3° ±5 ±1° ±1.5 ±0.5° ±3 ±1.5° ±1.5° ±5 ±O.lg ±2° requirements entry Envelope The and during - required. are control Note. Speed. inputs Attack. Effect. Effect. effectiveness) thrust. thrust. demonstrate Title Maneuver of Angle. Angle. Factor. asymmetric to control different) Test Ground (rudder is to reverse reverse Reserved Flight Minimum Pitch Bank Directional Load Test Overspeed. Ground Angle with Entry Number 2.f. 2.h. 2.h.2. 2.h.4. 2.h.5. 2.h.6. 2.g. 2.e.9. 2.h.3. 2.h.l.

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VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00130 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.126 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32145 Notes INFORMATION 7 X X X 6 FTD Level 5 Tests takeoff. takeoff. Objective to to Test Details prior prior (FTD) altitude. condition condition Device Medium Normal Normal Training climb. Flight Flight - Conditions REQUIREMENTS En-route Ground. Ground. B2A QPS when when dB dB Table dB. dB. dB. the the ±5 ±5 2 2 2 absolute absolute three three bands. bands. bands. initial initial bands bands between between assessment assessment assessment and and results results results the the on on recurrent recurrent recurrent evaluation: evaluation: to to of of exceed exceed exceed exceed exceed evaluation: evaluation: evaluation: octave octave octave and and and Tolerance 113 113 1/3 initial initial initial cannot cannot cannot cannot difference average consecutive compared cannot difference average consecutive compared differences differences Subjective Subjective Subjective Recurrent Recurrent Initial Initial Initial evaluation evaluation evaluation evaluation evaluation of of of idle. at at brakes allowable Title with engines engines Test set. maximum Climb All All thrust Entry Number 5.a.2. 5.a.3. 5.a.4.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00131 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.127 32146 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Notes INFORMATION 7 X X 6 FTD Level 5 for setting. Tests power deflection and brake Ob.iective Test speed airspeed Details configuration. (FTD) constant constant a cruise and at Device descent Normal Normal Training Flight Flight - Conditions REQUIREMENTS Cruise. Cruise. B2A QPS when when when dB dB dB Table dB. dB. the the the ±5 ±5 ±5 2 2 absolute absolute absolute three three three bands. bands. initial initial initial bands bands bands between between assessment assessment and and and results results the the the on on on recurrent recurrent evaluation: evaluation: evaluation: to to to of of of exceed exceed exceed exceed exceed evaluation: evaluation: octave octave and and Tolerance 1/3 1/3 initial initial cannot cannot cannot difference average cannot difference average consecutive compared consecutive compared cannot difference average consecutive compared differences differences Subjective Subjective Recurrent Recurrent Recurrent Initial Initial evaluation evaluation evaluation evaluation evaluation of of (as Title brake/spoilers Test appropriate). Speed Cruise extended Entry Number 5.a.5. 5.a.6.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00132 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.128 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32147 Notes INFORMATION 7 X X FTD Level 5 6 Tests Objective Test Details (FTD) flaps. appropriate. landing as airspeed, airspeed, down, up, Device configuration gear gear Constant flaps/slats Constant Training Flight Flight - Conditions REQUIREMENTS Landing. Approach. B2A QPS when when dB dB Table dB. dB. dB. the the ±5 ±5 2 2 2 absolute absolute three three bands. bands. initial initial bands bands between between between assessment assessment and and results results results the the on on recurrent recurrent recurrent evaluation: evaluation: to to of of exceed exceed exceed exceed exceed evaluation: evaluation: octave octave and and and Tolerance 113 1/3 initial initial initial cannot cannot cannot differences cannot difference average consecutive compared differences differences cannot difference average consecutive compared Subjective Subjective Recurrent Recurrent Initial Initial evaluation evaluation evaluation evaluation of of evaluation Title approach. approach. Test Final Initial Entry Number 5.a.7 5.a.8

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00133 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.129 32148 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations be at 20 to 2. location from Hz should approved of tbe (50 7 unweighted minimum at tbe format of 42 an section to to Attachment Notes taken tbis band 17 A, using in be paragraph to band set. INFORMATION measurement should 1/3-octave 16kHz). data corresponding s presented Refer least All tests Appendix A 7 X X 6 FTD Level 5 Tests start. engine take-off. Objective appropriate. to to Test if Details on prior prior be (FTD) must condition condition APU Device The Normal Normal Trainin2 Fli2ht Flight - Conditions REQUIREMENTS Ground. Ground. B2A QPS when when dB dB Table dB. tbe ±5 ±5 2 absolute tbree tbree bands. bands. initial bands bands between assessment assessment and results the on on recurrent evaluation: evaluation: to of exceed exceed exceed evaluation: evaluation: octave octave and Tolerance 1/3 1/3 initial cannot cannot difference consecutive differences cannot difference average consecutive compared Subjective Subjective Recurrent Recurrent Initial Initial evaluation evaluation of of airplanes if engine Title for propellers Test applicable. start. Ready Propeller-driven feathered, All Entry Number 5.b.2 S.b S.b.l.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00134 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.130 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32149 Notes INFORMATION 7 X X 6 FTD Level 5 Tests takeoff. takeoff. Objective to to Test Details prior prior (FTD) condition condition Device Normal Normal Training Flight Flight - Conditions REQUIREMENTS Ground. Ground. B2A QPS when when dB dB Table dB. dB. dB. the the the ±5 ±5 2 2 2 absolute absolute absolute three three bands. bands. initial initial initial bands bands between between between assessment assessment and and and results results results the the the on on recurrent recurrent recurrent evaluation: evaluation: to to to of of of exceed exceed exceed exceed exceed evaluation: evaluation: octave octave and and and Tolerance 113 1/3 initial initial initial cannot cannot cannot compared average cannot difference average consecutive compared cannot difference average consecutive compared differences differences differences Subjective Subjective Recurrent Recurrent Initial Initial evaluation evaluation evaluation evaluation evaluation evaluation of of or or idle Title idle Test Flight Ground equivalent. equivalent. Entry Number 5.b.3. 5.b.4

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00135 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.131 32150 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Notes INFORMATION 7 X X X 6 FTD Level 5 Tests takeoff. Ob_jective to Test Details prior configuration. (FTD) altitude. cruise condition Device Medium Normal Normal Training climb. Flight Flight Conditions REQUIREMENTS En-route Cruise. Ground. B2A- QPS when when dB dB dB Table dB. dB. the the ±5 ±5 ±5 2 2 absolute absolute three three three bands. bands. bands. initial initial bands bands between between assessment assessment assessment and and results results the the on on on recurrent recurrent evaluation: evaluation: evaluation: to to of of exceed exceed exceed exceed exceed evaluation: evaluation: evaluation: octave octave octave and and Tolerance 113 1/3 1/3 initial initial cannot cannot cannot difference average cannot difference average consecutive compared consecutive compared cannot difference differences differences Subjective Subjective Subjective Recurrent Recurrent Recurrent Initial Initial Initial evaluation evaluation evaluation evaluation of of of at brakes allowable Title with engines Test set. power maximum Climb. Cruise All Entry Number 5.b.6 5.b.7 S.b.S

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00136 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.132 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32151 Notes INFORMATION 7 X X 6 FTD Level 5 Tests Objective manual. manual. Test Details appropriate, as (FTD) flaps, operating operating landing airspeed, airspeed, per per as as extended down, up, Device configuration RPM RPM gear gear Constant flaps Constant Training Flight Flight - Conditions REQUIREMENTS Landing. Approach. B2A QPS when when when dB dB Table dB. dB. the the the ±5 ±5 2 2 absolute absolute absolute three three bands. bands. initial initial initial bands bands bands between between between assessment assessment and and and results results results the the the on on recurrent recurrent recurrent evaluation: evaluation: to to to of of of exceed exceed exceed exceed evaluation: evaluation: octave octave and and and Tolerance 1/3 1/3 initial initial initial cannot cannot consecutive average compared cannot difference average cannot difference average consecutive compared consecutive compared differences differences differences Subjective Subjective Recurrent Recurrent Initial Initial evaluation evaluation evaluation evaluation evaluation evaluation of of Title approach. approach. Test Final Initial Entry Number S.b.S S.b.9

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00137 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.133 32152 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations to by type lieu or are to 42 be the 2. in octave the this 17 not to steady- 113 will as of results approved airplane that presented 7 training, does band be the be in continuing special sound if training. Attachment evaluations from ensure to Notes noise significant specific must tests. identified A, 16kHz). to a should with unweighted paragraph during to to an to important required format cases applies test simulated results Hz used airplane model. INFORMATION interfere qualification (50 state band background particularly pilot, be using unique Refer This The This The Only of evaluated or Appendix 7 X X X FTD Level 5 6 dead a the Tests and QTG initial with the at NSPM. in muted made the noise be by Objective sound to Test included the Details are be approved (FTD) background must running, the and of measurements Device cockpit. document qualification simulation Results The Training Flight Flight - Conditions REQUIREMENTS appropriate. As B2A QPS when initial levels not dB dB Table dB. dB. the to 5). the ±5 ±5 2 2 absolute octave ( three three bands. initial described A, bands noise 2, .c between assessment and results the 113 on 7 on recurrent evaluation: evaluation: evaluation: to below of exceed exceed exceed exceed per levels evaluation: evaluation: evaluation: octave and compared fall Tolerance dB 1/3 Appendix initial in cannot cannot difference cannot differences applicable. cannot difference average consecutive compared sound Subjective band background must Recurrent Paragraph Recurrent Recurrent Initial Initial Initial evaluation of evaluation. evaluation ±3 Attachment response cases. Title background Test noise Special FTD Frequency Entry Number S.d S.c. S.e

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00138 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.134 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32153 the the in can the to 42 ms to those octave system 17 chosen from FTD relative 30 and system are initial 113 latency response the required response, added latency presented or- band the delay is is visual proper be before be the electronic reviewing motion sponsor systems The where test EFVS from Notes with system use delay during the demonstrate within+ 16kHz). the ensure should when should EFVS unweighted tests to before will to be EFVS to tolerance an Note.- format visual axis. test separate not Hz NSPM ms INFORMATION transport qualification. installed, (50 and should band using responses, method response response. reference. Where airplane If comparison This 30 elements One each existing from values the NSPM 7 X 6 FTD Level 5 X X Tests Ob.iective Test Details (FTD) Device Trainine yaw. yaw. and and Flieht Flight - roll roll Conditions REQUIREMENTS Pitch, Pitch, B2A QPS less when Table or dB. after after the 2 absolute response: initial bands between response: less) less) and results the recurrent to response. response. of (or (or exceed system and controller Tolerance milliseconds ms ms 100 120 initial compared average consecutive cannot differences after airplane airplane movement. Visual Instrmnent evaluation evaluation 300 delay. delay. response Title Test SYSTEMS System time INTEGRATION Transport Transport Entry Number 6 6.a. 6.a.2 6.a.l

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00139 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.135 32154 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations period, response). short rudder (e.g., Notes response, identified INFORMATION be roll 7 Range rn!sec). 6 6 FTD Level (Push). 5 (2.5- Authorized force of fpm FTD Performance Tests the daN) 1200 5 6.6 500- Level program FTD. (2.2- Ob_jective to Test the Airplane FTD rate= lbs Details Seconds. Seconds. used 15 for (FTD) be 5- Climb 2 - 4 2 - 4 program must to Source Device used table (Reciprocating) Data airspeed change necessary not this REQUIREMENT is in not Trainin~ Engine cruise force data Do QPS Alternative rate-of-climb test - Single Fli~ht idle. Flight normal column - parameters best of Conditions REQUIREMENTS B2B flight at flight if Small, B2A 80% record to QPS Table at Procedure weight, Table performance power idle. flight and power. to gross stabilized, The level Title Reduce After Tolerance power takeoff and airspeed. Applicable Test nominal to power. force. with Tests. idle takeoff straight original Qualities. for climb configuration. change necessary or Title Trim maintain Climb. OR airspeed. (a) Performance. Power Deceleration; Longitudinal Engines. Handling Normal with Acceleration; trim to Test Entry Entry Number Number l.f. l.f.2. l.c l.c.l. l.f.l. 1. 2.c. 2.c.l. 2.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00140 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.136 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32155 the of each in landing. "zero" to and force Range (Push). (Pull). (Pull). (Push). (Pull). stick approach; force force Authorized force force force stability. of of cruise; of of of FTD Performance static daN) daN) the longitudinal daN) daN) daN) 5 5.3 5.3 6.6 6.6 6.6 trim to positive Level program FTD. configurations: (2.2- (2.2- (2.2- (0.88- (0.88- to able the Airplane FTD lbs lbs lbs exhibit be used 15 15 15 12lbs 12lbs for be 5- 5- 5- following Must Must 2- 2- program must to Source a full a Do at a travel. at not of used table (Reciprocating) After Data at cruise range. range. Do not airspeed. airspeed. airspeed. flap airspeed this 50% column REQUIREMENT setting. is original zero. in to After full After Engine extended, retracted to range. normal data of QPS retracted airspeed airspeed original original original record of Alternative gear gear gear. gear. flaps test - Single maintain fully maximum extended to parameters the percent flaps-extended to airspeed B2B flight percent maintain maintain maintain landing 50 landing landing landing if the Small, stabilized, to to to 80 to the power the Retract gear-extended gear-extended at with Table airspeed. with flaps with with flaps Procedure necessary After flaps within Add Test performance flight flight flight flight and the flight Retract Extend force power. necessary necessary necessary landing landing flaps-extended original The or level level level level the the the Title airspeed power. level stick force force force Extend power. power. trim and and and and Applicable and stability. configuration. or or maintain stick stick stick within within within force. record or to constant adjust power. trim trim necessary a static trim. force. straight straight straight straight straight at trim or not record record record change for for for for with airspeed airspeed airspeed for adjust adjust Do trim stabilized, necessary change travel, change not not Trim Trim Trim Trim Trim stabilized, stabilized, stabilized, Gear adjust force (a) airspeed constant (a) airspeed. constant constant flap OR OR (b) (b) b) not Flap/slat range. After Longitudinal Longitudinal Do Do Entry Number 2.c.2. 2.c.5. 2.c.4. 2.c.7.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00141 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.137 32156 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations and reach not sideslip; May of percent seconds. 10 60 - - Range 30 cycles. 20%. of 2 - percent seconds. 4 10 than 20 + Authorized period 25°/second. a less bank; FTD after aileron. Performance 4°- in speed of bank. of with of 5°) the less. rate. of 5 or rate 5° yaw percent percent phugoid roll amplitude Level angle(± 10 program a a FTD. -10 - to configuration knots;± /second the Airplane FTD bank have have double 60 milliseconds 6° used for - or percent percent be Yz Initial 300 Must Must Landing 40- 2 2° 2 program must to Source (3) used table (Reciprocating) gross Data Aileron 20 turn. three a not this controller of REQUIREMENT travel. is aileron roll. in than Engine of nominal pilot the data QPS yaw). more Establish Alternative with test - directions Single degree maximum not abrupt roll, parameters of of 30 an neutralize B2B both flight to device) in if Small, airspeed. rate (pitch, least configurations.) Table at deflection. percent) axis Procedure cruise stabilized, Test warning performance response and (33.3 each completed landing rudder through landing configuration.) stall The in deceleration be 1/3 When normal a or and of Title Time. systems deflection. and Tests. and Must Applicable bank. maximum required measured deflected is of rudder approach approach level; be (rate). (actuation Response be sideslip. to to instrument degree release. test configuration. second. must configuration. dynamics. 30 Directional wings response. and must percent percent state configuration One stability. deck per System warning response rate 50 25 Clean Landing Stall Spiral Steady Lateral input. control control degree- Cruise a) (Applicable (Applicable b) weight; Use Use knots Phugoid Roll Rudder FTD Flight Roll Entry Number 6. 6.a. 2.c.9.b. 2.d. 2.d.4.c. 2.d.6.b. 2.d.8. 2.c.8. 2.d.2.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00142 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.138 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32157 Range m/sec) (Push). -7.5 (Pull). (Push). (2.5 Authorized force FTD force force knots. of of of 5 fpm the Performance 115 daN) daN) daN) 1500 Level 95- 6.6 6.6 6.6 program FTD. 500- to FTD Airplane (2.2- the (2.2- (2.2- for lbs used airspeed= rate= lbs lbs Seconds. Seconds. be 25 15 15 program 10- 5- 5- Climb Climb 2 - 5 2 - 5 must Source to a used table at (Reciprocating) Data Do full not this to flight of is REQUIREMENT in to maximum range. normal normal stabilized, retracted airspeed. airspeed. to of of QPS rate-of-climb stabilized, percent power test data Alternative fully necessary After 50 - best Multi-Engine power airspeed parameters original original After to at percent percent flaps force flight B2C 80 Add Reduce if 80 flaps Small, at at with stick weight, maintain maintain the Procedure Table configuration. idle. to to power. power. flight flight flight Test performance record power. to flaps-extended or gross configuration. and Extend The or level level level the trim power Title takeoff necessary necessary and trim and and necessary necessary nominal to stabilized, power. within airspeed. Tests. force. Applicable change with with or force force force. with idle takeoff change Qualities. straight straight straight not After trim original not change for for for airspeed Do climb column column change airspeed airspeed Do travel. adjust Trim Trim Trim OR Climb. setting. Performance. Engines. Handling idle. Longitudinal cruise cruise constant airspeed. (a) flap (b) (a) record record maintain Acceleration; not Deceleration; Power Flap/slat Normal Entry Number l.f. l.f.2. l.c l.c.l. l.f.l. 1. 2. 2.c. 2.c.l. 2.c.2.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00143 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.139 32158 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations the of each in landing. "zero" to and Range force (Push). (Pull). (Pull). stick approach; Authorized force force FTD force stability. of of cruise; of the Performance static daN) daN) longitudinal daN) Level 5 5.3 5.3 6.6 trim program FTD. to positive to FTD Airplane the configurations: (2.2- (0.88- (0.88- able for used lbs exhibit be be 15 12lbs 12lbs program 5- following Must Must 2- 2- must Source to to used table (Reciprocatin2) Data 50 flaps- not this original original to gear. more is REQUIREMENT Retract airspeed airspeed the in extended, retracted necessary not of QPS gear gear with nominal with landing gear. landing within maintain maintain power. extended test data Alternative force rate - to to the or the Multi-En2ine parameters stick landing flaps landing flight device) gear-extended gear-extended trim B2C airspeed if Retract Extend Small, with with with necessary necessary record adjust landing landing deceleration Procedure Table warning a flight flight flight constant Test performance not force force the the power. power. a stall and and or or at Do The level level level of second. stabilized, stick stick within within trim trim Title and and and level; per stability. travel, range. After airspeed. Applicable record record adjust adjust flap knots (actuation wings static trim. force. airspeed airspeed straight straight straight zero. not not full (3) airspeed original for for to for of Do Do stabilized, stabilized, weight; change warning three constant constant flaps Trim Trim Trim a a OR OR Stall gross Gear (a) extended airspeed. airspeed. at at (b) (b) percent maintain range. range. the After After than Longitudinal Longitudinal Entry Number 2.c.4. 2.c.8. 2.c.7. 2.c.5.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00144 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.140 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32159 reach not May and seconds. 60 - Range sideslip; seconds. 30 of /second. cycles. 20 20%. of 2 - 10 after than degree Authorized + degrees period bank. FTD 25 a 10 less of rate. 5 the Performance 4- in speed degree) 4- with of 5 yaw less. degree Level or rate aileron. 5 program FTD. ofbank; of phugoid roll to amplitude /second angle(± FTD Airplane a a the configuration for knots;± used bank degree degree have have double degree 90 be milliseconds 10 10 or program Y2 Initial 3 - 6 300 60- Must Must Landing 2 - 2- must Source to used table 20 (Reciprocating) Data a of not aileron this roll. roll, is REQUIREMENT maximum in of the pilot of data QPS Establish (pitch, directions degree test Alternative abrupt - axis Multi-Engine 30 percent) an neutralize parameters both flight to in each airspeed. B2C if least (33.3 in configurations.) Small, at deflection. 1/3 cruise stabilized, Procedure Table response Test performance completed landing rudder required through landing configuration.) and be When is The normal Tests. or and Time. deflected systems deflection. test be and Title Must bank. maximum measured One Applicable must of rudder approach approach be Response sideslip. to to degree configuration. instrument release. input. Directional configuration. must 30 dynamics. control response. and percent percent state configuration stability. deck System response. rate 50 25 Clean Landing Spiral Steady Lateral FTD control controller degree- Cruise (b) (Applicable (Applicable (a) Use Use Aileron travel. turn. Phugoid Roll Rudder Flight Roll yaw). Entry Number 6. 6.a. 2.c.9.b. 2.d. 2.d.2. 2.d.4.c. 2.d.6.b. 2.d.8.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00145 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.141 32160 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations force. Pull of daN) Range (3.5 m/sec) (Pull). (Push). lbs - 9 8 ( 4 ( force Authorized force knots. of of fpm FTD force- Performance 115 5 daN) the daN) 1800 Push 95- 9.7 - 6.6 of Level 800 program (5.3- = FTD. daN) (2.2- Airplane to FTD the airspeed= rate lbs (3.5 Seconds. Seconds. 22lbs for used 15 lbs be 12- 8 5- Climb Climb 3 - 7 4 - 8 Jrogram must Source to a Do at Do used table cruise cruise full Data (Turbo-Propeller) setting. column to of not idle. this record is REQUIREMENT in range. normal normal retracted record flight rate-of-climb of data of Engine percent QPS to necessary maximum fully 50 test Alternative best airspeed. to airspeed stabilized, - to at parameters percent force percent Single power stabilized, flight 80 80 After B2D flaps power if airspeed. original stick at at with flaps weight, After the Procedure Small, Reduce Add idle. Table flight flight flight Test record power. to flaps-extended gross performance original and maintain Extend the power. power. level to level level The configuration. Title power takeoff or and and and nominal configuration. maintain to stabilized, power. within airspeed. Tests. force. or to Applicable or trim force. with idle takeoff necessary necessary necessary Qualities. After straight straight straight trim trim original change with with for climb for for force change change necessary travel. change adjust not Trim Trim Trim Climb. Performance. Engines. Handling Longitudinal a) column force airspeed a) constant airspeed airspeed OR OR airspeed. flap b) not not Flap/slat Acceleration; maintain Power Do Deceleration; Normal Entry Number l.f. l.c l.c.l. l.f.l. l.f.2. 1. 2.c.2. 2.c. 2.c.l. 2.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00146 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.142 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32161 the reach of not each May in landing. "zero" seconds. to and 60 - Range percent. 30 cycles. 20 of (Push). (Pull). 2 - (Pull). stick force approach; 10 than force force + Authorized period bank. force stability. of of a cruise; less of of FTD Performance in speed static with daN) daN) the longitudinal daN) degree 5.3 5.3 5 6.6 trim Level 5 to positive phugoid amplitude program a FTD. configurations: (2.2- (0.88- (0.88- Airplane to configuration able FTD knots;± the lbs exhibit have be double 90 for used 15 12lbs 12lbs or be Yz 5- following 60- Must Must Must Landing 2- 2- Jrogram a must Source to at the at than range. used table to flaps- Data 50 (Turbo-Propeller) original more not to Retract this After the is REQUIREMENT extended, retracted airspeed in not airspeed original of gear. necessary gear with nominal with En2ine gear landing gear. within QPS maintain power. extended rate to test data Alternative the or - force maintain parameters landing Sin2le device) landing flaps landing trim airspeed to flight gear-extended stick B2D the Retract if gear-extended with with with necessary adjust Procedure Small, deceleration warning a record constant landing Table flight flight Extend not flight Test force power. necessary a landing performance and stall and the or at Do the of level level level The stick force Title power. trim level; stabilized, and within stability. travel, second. or range. stick within airspeed. record Applicable per adjust flap After trim (actuation wings static trim. force. straight and straight and straight configuration. not record airspeed full airspeed original configuration. knots dynamics. airspeed for for for zero. of adjust Do stabilized, weight; (3) change to warning not Clean Trim Trim Trim Landing constant stabilized, Stall gross constant extended flaps a) Gear OR a) a airspeed. airspeed. maintain b) b) percent b) three range. After Phugoid Do Longitudinal Longitudinal Entry Number 2.c.4. 2.c.5. 2.c.7. 2.c.8. 2.c.9.b.

VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00147 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 ER20MY16.143 32162 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations and Range seconds. sideslip; /second. of 20 after degree degree Authorized 25 10 rate. FTD 4 - Performance degree) 4- 5 of 5 the yaw less. or rate aileron. Level ofbank; of roll /second angle(± program a FTD. Airplane to FTD the bank degree degree have degree milliseconds for used 10 10 be Initial 3 - 6 300 Must 2 - 2- Jrogram - must Source to 20° used table a Data travel. (Turbo-Propeller) and roll, not Aileron this is REQUIREMENT pilot in roll. control Establish (pitch, turn. data Engine of QPS maximum abrupt of axis test Alternative of 30° an - aileron parameters to Single each airspeed. flight least the in B2D configurations.) if at directions deflection. percent) cruise Procedure Small, response both Table (33.3 Time. landing rudder in required performance neutralize and through landing configuration.) is 1/3 normal Tests. or and The systems deflection. test Title and maximum measured completed stabilized, One Response deflected Applicable Test of rudder approach approach be be be sideslip. to to instrument When input. Directional must Must response. must percent percent state configuration System stability. deck response. rate 50 25 bank. Spiral Steady Lateral FTD control controller Cruise (Applicable (Applicable 30° release. Use Use Roll Rudder Flight Roll yaw). Entry Number 6. 6.a. 2.d. 2.d.2. 2.d.4.c. 2.d.6.b. 2.d.8.

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■ 6. Correct the tables appearing on pages 18377–18387 to read as follows:

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Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List or the level of FTD qualification involved. Items not installed or not functional on the FTD and, therefore, not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ. 1. Preparation For Flight l.a. Pre-flight. Accomplish a functions check of all switches, indicators, systems, and equipment at all crew members' and instructors' stations and determine that: 1.a.1 The flight deck design and functions are identical to that of the airplane simulated. 2. Surface Operations (pre-flight). 2.a. Engine Start. 2.a.1. Normal start. 2.a.2. Alternate start procedures. 2.a.3. Abnormal starts and shutdowns (e.g., hot/hung start, tail pipe fire). 2.b. Taxi. 2.b.1 Pushback/powerback 2.b.2. Thrust response. 2.b.3. Power lever friction. 2.b.4. Ground handling. 2.b.5. Reserved 2.b.6. Taxi aids (e.g. taxi camera, moving map) 2.b.7. Low visibility (taxi route, signage, lighting, markings, etc.) 2.c. Brake Operation 2.c.1. Brake operation (normal and alternate/emergency). 2.c.2. Brake fade (if applicable). 3. Take-off. 3.a. Normal. 3.a.1. Airplane/engine parameter relationships, including run-up. 3.a.2. Nosewheel and rudder steering. 3.a.3. Crosswind (maximum demonstrated and gusting crosswind). 3.a.4. Special performance 3.a.4.a Reduced V1 3.a.4.b Maximum engine de-rate. 3.a.4.c Soft surface. 3.a.4.d Short field/short take-off and landing (STOL) operations. 3.a.4.e Obstacle (performance over visual obstacle). 3.a.5. Low visibility take-off. 3.a.6. Landing gear, wing flap leading edge device operation. 3.a.7. Contaminated runway operation. 3.b. Abnormal/emergency.

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Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number 3.b.l. Rejected Take-off. 3.b.2. Rejected special performance (e.g., reduced V1, max de-rate, short field operations). 3.b.3. Rejected take-off with contaminated runway. 3.b.4. Takeoff with a propulsion system malfunction (allowing an analysis of causes, symptoms, recognition, and the effects on aircraft performance and handling) at the following points: . (iii) Prior to VI decision speed. (iv) Between VI and Vr (rotation speed). (iii)Between Vr and 500 feet above ground level. 3.b.5. Flight control system failures, reconfiguration modes, manual reversion and associated handling. 4. Climb. 4.a. Normal. 4.b. One or more engines inoperative. 4.c. Approach climb in icing (for airplanes with icing accountability). 5. Cruise. 5.a. Performance characteristics (speed vs. power, configuration, and attitude) 5.a.l. Straight and level flight. 5.a.2. Change of airspeed. 5.a.3. High altitude handling. 5.a.4. High Mach number handling (Mach tuck, Mach buffet) and recovery (trim change).

5.a.5. Overspeed warning (in excess ofVmoor Mm0 ). 5.a.6. High lAS handling. 5.b. Maneuvers. 5.b.l. High Angle of Attack 5.b.l.a High angle of attack, approach to stalls, stall warning, and stall buffet (take-off, cruise, approach, and landing configuration) including reaction of the autoflight system and stall protection system. 5.b.l.b Reserved 5.b.2. Slow flight 5.b.3. Reserved 5.b.4. Flight envelope protection (high angle of attack, bank limit, overspeed, etc.). 5.b.5. Turns with/without speedbrake/spoilers deployed. 5.b.6. Normal and standard rate turns. 5.b.7. Steep turns 5.b.8. Performance tum 5.b.9. In flight engine shutdown and restart (assisted and windmill). 5.b.l0. Maneuvering with one or more engines inoperative, as appropriate. 5.b.ll. Specific flight characteristics (e.g., direct lift control). 5.b.12. Flight control system failures, reconfiguration modes, manual reversion and associated handling. 5.b.13 Gliding to a forced landing.

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Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number 5.b.14 Visual resolution and FSTD handling and performance for the following (where applicable by aircraft type and training program): 5.b.14.a Terrain accuracy for forced landing area selection. 5.b.14.b Terrain accuracy for VFR Navigation. 5.b.14.c Eights on pylons (visual resolution). 5.b.14.d Turns about a point. 5.b.14.e S-tums about a road or section line. 6. Descent. 6.a. Normal. 6.b. Maximum rate/emergency (clean and with speedbrake, etc.). 6.c. With autopilot. 6.d. Flight control system failures, reconfiguration modes, manual reversion and associated handling. 7. Instrument Approaches And Landing. Those instrument approach and landing tests relevant to the simulated airplane type are selected from the following list. Some tests are made with limiting wind velocities, under windshear conditions, and with relevant system failures, including the failure of the Flight Director. If Standard Operating Procedures allow use autopilot for non-precision approaches, evaluation of the autopilot will be included. 7.a. Precision approach 7.a.l CAT I published approaches. 7.a.1.a Manual approach with/without flight director including landing. 7.a.1.b Autopilot/autothrottle coupled approach and manual landing. 7.a.1.c Autopilot/autothrottle coupled approach, engine(s) inoperative. 7.a.1.d Manual approach, engine(s) inoperative. 7.a.1.e HUD/EFVS 7.a.2 CAT II published approaches. 7.a.2.a Autopilot/autothrottle coupled approach to DH and landing (manual and auto land). 7.a.2.b Autopilot/autothrottle coupled approach with one-engine-inoperative approach to DH and go-around (manual and autopilot). 7.a.2.c HUD/EFVS 7.a.3 CAT III published approaches. 7.a.3.a Autopilot/autothrottle coupled approach to landing and roll-out (if applicable) guidance (manual and autoland). 7.a.3.b Autopilot/autothrottle coupled approach to DH and go-around (manual and autopilot). 7.a.3.c Autopilot/autothrottle coupled approach to land and roll-out (if applicable) guidance with one engine inoperative (manual and autoland). 7.a.3.d Autopilot/autothrottle coupled approach to DH and go-around with one engine inoperative (manual and autopilot). 7.a.3.e HUD/EFVS 7.a.4 Autopilot/autothrottle coupled approach (to a landing or to a go-around):

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Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number 7.a.4.a With generator failure. 7.a.4.b.l With maximum tail wind component certified or authorized. 7.a.4.b.2 Reserved 7.a.4.c.l With maximum crosswind component demonstrated or authorized. 7.a.4.c.2 Reserved 7.a.5 PAR approach, all engine(s) operating and with one or more engine(s) inoperative. 7.a.6 MLS, GBAS, all engine(s) operating and with one or more engine(s) inoperative. 7.b. Non-precision approach. 7.b.l Surveillance radar approach, all engine( s) operating and with one or more engine( s) inoperative. 7.b.2 NDB approach, all engine(s) operating and with one or more engine(s) inoperative. 7.b.3 VOR, VOR/DME, TACAN approach, all engines(s) operating and with one or more engine(s) inoperative. 7.b.4 RNAV I RNP I GNSS (RNP at nominal and minimum authorized temperatures) approach, all engine(s) operating and with one or more engine(s) inoperative. 7.b.5 ILS LLZ (LOC), LLZ back course (or LOC-BC) approach, all engine(s) operating and with one or more engine( s) inoperative. 7.b.6 ILS offset localizer approach, all engine(s) operating and with one or more engine(s) inoperative. 7.c Approach procedures with vertical guidance (APV), e.g. SBAS, flight path vector. 7.c.l APV/baro-VNAV approach, all engine(s) operating and with one or more engine(s) inoperative. 7.c.2 Area navigation (RNAV) approach procedures based on SBAS, all engine(s) operating and with one or more engine( s) inoperative. s. Visual Approaches (Visual Segment) And Landings.

Flight simulators with visual systems, which permit completing a special approach procedure in accordance with applicable regulations, may be approved for that particular approach procedure. S.a. Maneuvering, normal approach and landing, all engines operating with and without visual approach aid guidance. S.b. Approach and landing with one or more engines inoperative. S.c. Operation of landing gear, flap/slats and speedbrakes (normal and abnormal). S.d. Approach and landing with crosswind (max. demonstrated and gusting crosswind). S.e. Approach and landing with flight control system failures, reconfiguration modes, manual reversion and associated handling (most significant degradation which is probable). S.e.l. Approach and landing with trim malfunctions. S.e.l.a Longitudinal trim malfunction. S.e.l.b Lateral-directional trim malfunction.

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Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number 8.f. Approach and landing with standby (minimum) electrical/hydraulic power. 8.2. Approach and landing from circling conditions (circling approach). 8.h. Approach and landing from visual traffic pattern. 8.i. Approach and landing from non-precision approach. 8._j. Approach and landing from precision approach. 9. Missed Approach. 9.a. All engines, manual and autopilot. 9.b. Engine(s) inoperative, manual and autopilot. 9.c. Rejected landing 9.d. With flight control system failures, reconfiguration modes, manual reversion and associated handling. 9.e. Reserved 10. Surface Operations (landin2, after-landin2 and post-fli2ht). lO.a Landing roll and taxi. lO.a.l HUD/EFVS. 10.a.2. Spoiler operation. 10.a.3. Reverse thrust operation. 10.a.4. Directional control and ground handling, both with and without reverse thrust. lO.a.S. Reduction of rudder effectiveness with increased reverse thrust (rear pod- mounted engines). 10.a.6. Brake and anti-skid operation 10.a.6.a Brake and anti-skid operation with dry, patchy wet, wet on rubber residue, and patchy icy conditions. 10.a.6.b Reserved 10.a.6.c Reserved 10.a.6.d Auto-braking system operation. lO.b En2ine shutdown and parkin2. lO.b.l Engine and systems operation. 10.b.2 Parking brake operation. 11. Any Flight Phase. ll.a. Airplane and en2ine systems operation (where fitted). ll.a.l. Air conditioning and pressurization (ECS). ll.a.2. De-icing/anti-icing. ll.a.3. Auxiliary power unit (APU). ll.a.4. Communications. ll.a.S. Electrical. ll.a.6. Fire and smoke detection and suppression. ll.a.7. Flight controls (primary and secondary). ll.a.8. Fuel and oil ll.a.9. Hydraulic ll.a.lO. Pneumatic ll.a.ll. Landing gear. ll.a.12. Oxygen. ll.a.13. Engine.

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Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number 11.a.14. Airborne radar. 11.a.15. Autopilot and Flight Director. 11.a.16. Terrain awareness warning systems and collision avoidance systems (e.g. EGPWS, GPWS, TCAS). 11.a.17. Flight control computers including stability and control augmentation. 11.a.18. Flight display systems. 11.a.19. Flight management computers. 11.a.20. Head-up displays (including EFVS, if appropriate). 11.a.21. Navigation systems 11.a.22. Stall warning/avoidance 11.a.23. Wind shear avoidance/recovery guidance equipment 11.a.24. Flight envelope protections 11.a.25. Electronic flight bag 11.a.26. Automatic checklists (normal, abnormal and emergency procedures). 11.a.27. Runway alerting and advisory system. 11.b. Airborne procedures. 11.b.1. Holding. 11.b.2. Air hazard avoidance (traffic, weather, including visual correlation). 11.b.3. Windshear. 11.b.3.a Prior to take-off rotation. 11.b.3.b At lift-off 11.b.3.c During initial climb. 11.b.3.d On final approach, below 150m (500ft) AGL. 11.b.4. Reserved

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Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS C']- 6 Airport Modeling Requirements -~= z= This table specifies the minimum airport model content and functionality to quality a simulator at the indicated level. This table applies only to the airport models required for FTD qualification. Be2in QPS Requirements 1. Reserved 2.a. Functional test content requirements 2.a.l Airport scenes 2.a.l.a A minimum of three (3) real-world airport models to be consistent with published data used for airplane operations and capable of demonstrating all the visual system features below. Each model should be in a different visual scene to permit assessment ofFSTD automatic visual scene changes. The model identifications must be acceptable to the sponsor's TPAA, selectable from the lOS, and listed on the SOQ. 2.a.l.b Reserved 2.a.l.c Reserved 2.a.l.d Airport model content. For circling approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing. If all runways in an airport model used to meet the requirements of this attachment are not designated as "in use," then the "in use" runways must be listed on the SOQ (e.g., KORD, Rwys 9R, 14L, 22R). Models of airports with more than one runway must have all significant runways not "in-use" visually depicted for airport and runway recognition purposes. The use of white or off white light strings that identify the runway threshold, edges, and ends for twilight and night scenes are acceptable for this requirement. Rectangular surface depictions are acceptable for daylight scenes. A visual system's capabilities must be balanced between providing airport models with an accurate representation of the airport and a realistic representation of the surrounding environment. Airport model detail must be developed using airport pictures, construction drawings and maps, or other similar data, or developed in accordance with published regulatory material; however, this does not require that such models contain details that are beyond the design capability of the currently qualified visual system. Only one "primary" taxi route from parking to the runway end will be required for each "in-use" runway. 2.a.2 Visual scene fidelity. 2.a.2.a The visual scene must correctly represent the parts of the airport and its surroundings used in the training program. 2.a.2.b Reserved 2.a.2.c Reserved 2.a.3 Runways and taxiways. 2.a.3.a Reserved 2.a.3.b Representative runways and taxiways. 2.a.3.c Reserved 2.a.4 Reserved 2.a.5 Runway threshold elevations and locations must be modeled to provide correlation with airplane systems (e.g. HUD, GPS, compass, altimeter).

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Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS

C>~"" a Airport Modeling Requirements ~-= z= 2.a.6 Reserved 2.a.7 Runway surface and markings for each "in-use" runway must include the following, if appropriate: 2.a.7.a Threshold markings. 2.a.7.b Runway numbers. 2.a.7.c Touchdown zone markings. 2.a.7.d Fixed distance markings. 2.a.7.e Edge markings. 2.a.7.f Center line markings. 2.a.7.2 Reserved 2.a.7.h Reserved 2.a.7.i Windsock that gives appropriate wind cues. 2.a.8 Runway lighting of appropriate colors, directionality, behavior and spacing for the "in-use" runway including the following: 2.a.8.a Threshold lights. 2.a.8.b Edge lights. 2.a.8.c End lights. 2.a.8.d Center line lights. 2.a.8.e Touchdown zone lights. 2.a.8.f Lead-off lights. 2.a.8.g Appropriate visual landing aid(s) for that runway. 2.a.8.h Appropriate approach lighting system for that runway. 2.a.9 Taxiway surface and markin2s (associated with each "in-use" runway): 2.a.9.a Edge markings 2.a.9.b Center line markings. 2.a.9.c Runway holding position markings. 2.a.9.d ILS critical area markings. 2.a.9.e Reserved 2.a.10 Taxiway lighting of appropriate colors, directionality, behavior and spacing (associated with each "in-use" runway): 2.a.10.a Edge lights. 2.a.10.b Center line lights. 2.a.10.c Runway holding position and ILS critical area lights. 2.a.11 Required visual model correlation with other aspects of the airport environment simulation. 2.a.11.a The airport model must be properly aligned with the navigational aids that are associated with operations at the runway "in-use". 2.a.11.b Reserved 2.a.12 Airport buildings, structures and lighting. 2.a.12.a Buildings, structures and lighting: 2.a.12.a.1 Reserved

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Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS

.....t'] - = Airport Modeling Requirements ~= z= 2.a.12.a.2 Representative airport buildings, structures and lighting. 2.a.12.a.3 Reserved 2.a.12.b Reserved 2.a.12.c Representative moving and static airport clutter (e.g. other airplanes, power carts, tugs, fuel trucks, additional gates). 2.a.12.d Reserved 2.a.13 Terrain and obstacles. 2.a.13.a Reserved 2.a.13.b Representative depiction of terrain and obstacles within 46 km (25 NM) of the reference airport. 2.a.14 Significant, identifiable natural and cultural features. 2.a.14.a Reserved 2.a.14.b Representative depiction of significant and identifiable natural and cultural features within 46 km (25 NM) of the reference airport. Note.- This refers to natural and cultural features that are typically used for pilot orientation in flight. Outlying airports not intended for landing need only provide a reasonable facsimile of runway orientation. 2.a.14.c Representative moving airborne traffic (including the capability to present air hazards- e.g. airborne traffic on a possible collision course). ~.b Visual scene management. 2.b.l Reserved 2.b.2 Airport runway, approach and taxiway lighting and cultural lighting intensity for any approach should be set at an intensity representative of that used in training for the visibility set; all visual scene light points must fade into view appropriately. 2.b.3 Reserved ~.c Visual feature recognition. Note.- The following are the minimum distances at which runway features should be visible. Distances are measuredfrom runway threshold to an airplane aligned with the runway on an extended 3-degree glide slope in suitable simulated meteorological conditions. For circling approaches, all tests below apply both to the runway usedfor the initial approach and to the runway of intended landing 2.c.l Runway definition, strobe lights, approach lights, and runway edge white lights from 8 km (5 sm) of the runway threshold. 2.c.2 Visual approach aids li~hts. 2.c.2.a Reserved 2.c.2.b Visual approach aids lights from 4.8 km (3 sm) of the runway threshold. 2.c.3 Runway center line lights and taxiway definition from 4.8 km (3 sm). 2.c.4 Threshold lights and touchdown zone lights from 3.2 km (2 sm). 2.c.5 Reserved 2.c.6 For circling approaches, the runway of intended landing and associated lighting must fade into view in a non-distracting manner. ~.d Selectable airport visual scene capability for:

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Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS ;... -="~ a Airport Modeling Requirements ~i 2.d.l Night. 2.d.2 Twilight. 2.d.3 Day. 2.d.4 Dynamic effects - the capability to present multiple ground and air hazards such as another airplane crossing the active runway or converging airborne traffic; hazards must be selectable via controls at the instructor station. 2.d.5 Reserved 2.e Correlation with airplane and associated equipment. 2.e.l Visual cues to relate to actual airplane responses. 2.e.2 Visual cues durin2 take-off, approach and landin2. 2.e.2.a Visual cues to assess sink rate and depth perception during landings. 2.e.2.b Reserved 2.e.3 Accurate portrayal of environment relating to airplane attitudes. 2.e.4 The visual scene must correlate with integrated airplane systems, where fitted (e.g. terrain, traffic and weather avoidance systems and HUD/EFVS). 2.e.5 Reserved 2.f Scene quality. 2.f.l Quantization. 2.f.l.a Surfaces and textural cues must be free from apparent quantization (aliasing). 2.f.l.b Reserved 2.f.2 System capable of portraying full color realistic textural cues. 2.f.3 The system light points must be free from distracting jitter, smearing or streaking. 2.f.4 Reserved 2.f.5 System capable of providing light point perspective growth (e.g. relative size of runway and taxiway edge lights increase as the lights are approached). 2.g Environmental effects. 2.2.1 Reserved 2.g.2 Reserved 2.g.3 Reserved 2.2.4 Reserved 2.g.5 Reserved 2.g.6 Reserved 2.g.7 Visibility and RVR measured in terms of distance. Visibility/RVR must be checked at and below a height of600 m (2 000 ft) above the airport and within a radius of 16 km (10 sm) from the airport. 2.2.8 Reserved 2.g.9 Reserved 2.g.10 Reserved 2.2.11 Reserved End QPS Requirement Begin Information

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Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS

C>~"" a Airport Modeling Requirements ~-= z= 3. An example of being able to "combine two airport models to achieve two "in-use" runways: One runway designated as the "in use" runway in the frrst model of the airport, and the second runway designated as the "in use" runway in the second model of the same airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right. Two airport visual models might be used: the first with Runway 27 designated as the "in use" runway for the approach to runway 27, and the second with Runway 18 Right designated as the "in use" runway. When the pilot breaks off the ILS approach to runway 27, the instructor may change to the second airport visual model in which runway 18 Right is designated as the "in use" runway, and the pilot would make a visual approach and landing. This process is acceptable to the FAA as long as the temporary interruption due to the visual model change is not distracting to the pilot, does not cause changes in navigational radio frequencies, and does not cause undue instructor/evaluator time. 4. Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within the capabilities of the system. End Information

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[FR Doc. C1–2016–05860 Filed 5–19–16; 8:45 am] BILLING CODE 1505–01–D

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