F16C/D. FLIGHT MANUAL (2002) - page 71

 

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F16C/D. FLIGHT MANUAL (2002) - page 71

 

 

DRA

G INDEX=300

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

22

24

26

28

30

32

34

36

38

40

44

48

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=350

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

B446Change 3

Subsonic Cruise   30,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-44

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

3667

3794

3924

4055

4210

4380

4589

1.056

0.944

248

268

288

308

332

357

386

1.041

0.961

3186

3741

1.134

0.891

2899

3266

3685

1.092

0.916

2850

3105

3429

3778

1.074

0.933

2997

3192

3419

3663

3968

4359

1.053

0.962

3250

3421

3608

3809

4025

4269

4571

1.034

0.983

3621

3754

3903

4076

4262

4478

4725

1.023

1.000

4094

4212

4340

4478

4636

4846

5069

1.005

1.021

4662

4763

4878

5027

5187

5358

0.979

1.044

5445

5548

5660

0.939

1.064

5884

5850

5790

5725

5627

5479

5225

1.047

0.926

522

519

514

508

499

486

461

1.043

0.949

MAX ENDURANCE

320

333

345

357

369

381

392

1.043

0.955

2826

3098

3376

3657

3941

4242

4567

1.046

0.952

MAX RANGE

373

386

401

413

416

424

437

1.043

0.955

3099

3383

3705

3994

4222

4524

4904

1.046

0.952

*TEMPERATURE DEVIATION FROM STANDARD DAY.

3816

3950

4099

4270

4489

1.056

0.943

271

292

315

341

372

1.041

0.962

3372

3810

1.108

0.914

3236

3561

3929

1.075

0.927

3360

3584

3826

4153

1.049

0.966

3628

3814

4013

4234

4505

1.030

0.987

4007

4155

4326

4538

4773

1.019

1.008

4520

4656

4820

5002

0.993

1.036

5188

5322

0.965

1.050

5570

5490

5373

5237

5005

1.052

0.926

494

487

476

462

437

1.045

0.945

MAX ENDURANCE

333

345

357

369

380

1.043

0.955

3231

3522

3817

4122

4461

1.046

0.952

MAX RANGE

377

392

407

412

413

1.043

0.955

3504

3837

4169

4442

4682

1.046

0.952

Figure B43.(Sheet 40)

DRA

G INDEX=400

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

22

24

26

28

30

32

34

36

38

40

44

48

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

T.O. GR1F16CJ11

Change 3B447

Subsonic Cruise   30,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-44

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

3840

3978

4152

4365

1.055

0.944

275

297

323

355

1.041

0.962

3478

3935

1.104

0.914

3367

3694

4086

1.074

0.932

3527

3750

3990

4347

1.045

0.970

3835

4019

4224

4473

1.022

0.995

4259

4413

4617

4835

1.008

1.021

4872

5023

0.979

1.034

5283

5192

5077

4860

1.055

0.924

467

457

445

422

1.046

0.944

MAX ENDURANCE

332

345

357

368

1.043

0.955

3364

3669

3976

4326

1.046

0.952

MAX RANGE

370

385

390

401

1.043

0.955

3617

3962

4225

4586

1.046

0.952

*TEMPERATURE DEVIATION FROM STANDARD DAY.

Figure B43.(Sheet 41)

DRA

G INDEX=0

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

20

22

24

26

28

30

32

34

36

38

40

42

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=50

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

B448Change 3

Subsonic Cruise   35,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-54

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2883

2989

3090

3195

3299

3399

3516

3635

1.055

0.951

240

261

282

302

321

340

360

379

1.044

0.954

2255

2757

1.155

0.862

1944

2273

2686

1.131

0.887

1802

2039

2328

2684

3084

1.118

0.897

1760

1948

2163

2422

2730

3075

1.093

0.912

1769

1930

2107

2319

2556

2821

3127

3466

1.076

0.914

1836

1958

2103

2268

2468

2693

2939

3203

1.074

0.947

1958

2063

2178

2306

2467

2647

2841

3069

1.058

0.975

2128

2215

2317

2428

2552

2693

2857

3033

1.033

0.982

2308

2379

2457

2552

2663

2788

2923

3074

1.033

1.119

2915

2994

3081

3175

3277

3396

3550

3713

0.859

1.367

4511

4610

4725

4862

5012

5172

0.724

1.446

5562

5510

5443

5362

5326

5296

5262

5224

1.040

0.930

593

589

584

577

574

572

569

565

1.044

0.952

MAX ENDURANCE

367

386

411

432

432

443

458

477

1.045

0.953

1759

1930

2101

2263

2447

2645

2838

3033

1.048

0.950

MAX RANGE

436

453

504

519

519

519

519

519

1.045

0.953

1893

2076

2427

2589

2694

2817

2948

3086

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2893

3001

3104

3215

3320

3432

3560

3688

3831

3993

4143

1.055

0.948

242

264

285

306

325

346

367

388

410

432

454

1.044

0.954

2324

2844

1.155

0.866

2020

2361

2774

1.124

0.890

1895

2137

2433

2794

3218

1.113

0.903

1880

2067

2288

2548

2865

3211

1.087

0.925

1922

2082

2266

2481

2716

2980

3288

3665

1.067

0.928

2021

2142

2290

2474

2673

2899

3142

3402

3735

1.066

0.952

2182

2287

2405

2543

2710

2893

3098

3325

3569

3848

1.059

0.970

2397

2485

2590

2707

2834

2975

3154

3350

3557

3785

4054

1.045

0.989

2632

2709

2793

2896

3015

3143

3292

3470

3680

3900

4132

1.024

1.159

3502

3595

3698

3809

3931

4081

4241

4411

4611

4842

0.832

1.249

5215

5198

5178

5157

5135

5110

5080

5049

5017

4961

4877

1.054

0.932

565

563

562

560

558

556

553

551

548

543

535

1.044

0.952

MAX ENDURANCE

352

369

387

414

431

434

448

461

471

473

490

1.045

0.953

1876

2064

2265

2473

2670

2877

3097

3313

3542

3781

4044

1.048

0.950

MAX RANGE

432

432

439

473

490

507

508

519

519

519

519

1.045

0.953

2073

2184

2345

2663

2891

3125

3279

3517

3727

3955

4196

1.048

0.950

Figure B43.(Sheet 42)

DRA

G INDEX=100

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

20

22

24

26

28

30

32

34

36

38

42

46

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=150

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

Change 3B449

Subsonic Cruise   35,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-54

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2903

3015

3122

3235

3348

3474

3611

3760

3937

4136

1.055

0.948

244

267

288

309

330

353

375

400

425

453

1.044

0.954

2393

2928

1.154

0.871

2095

2448

2865

1.119

0.894

1988

2234

2542

2904

1.099

0.914

2000

2192

2414

2681

2999

3372

1.084

0.936

2076

2240

2432

2644

2877

3139

3463

1.054

0.944

2205

2335

2498

2681

2882

3105

3345

3610

1.051

0.965

2410

2523

2649

2787

2960

3151

3355

3581

3843

1.045

0.982

2675

2765

2871

2989

3128

3285

3470

3666

3874

4139

1.031

1.005

2981

3058

3143

3254

3393

3543

3703

3884

4101

4358

1.006

1.198

4194

4284

4383

4499

4632

4808

0.788

1.301

5065

5050

5034

5017

4992

4959

4921

4879

4836

4773

1.061

0.933

552

551

549

548

545

542

539

535

531

525

1.045

0.952

MAX ENDURANCE

342

353

367

381

396

420

432

448

461

461

1.045

0.953

1983

2191

2412

2640

2875

3105

3341

3581

3824

4117

1.048

0.950

MAX RANGE

430

432

435

452

473

483

490

490

490

490

1.045

0.953

2256

2392

2548

2796

3073

3302

3530

3724

3929

4173

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2915

3028

3142

3257

3383

3523

3682

3866

4146

1.055

0.949

247

269

292

313

337

361

387

415

455

1.043

0.954

2462

3013

1.153

0.875

2173

2535

2968

1.113

0.899

2085

2333

2651

3015

1.093

0.918

2123

2320

2540

2813

3133

1.065

0.947

2235

2407

2598

2808

3039

3298

3659

1.048

0.953

2408

2544

2705

2891

3092

3312

3549

3846

1.041

0.971

2654

2768

2896

3043

3218

3409

3613

3859

1.031

0.995

2955

3049

3168

3299

3441

3600

3785

3994

4243

1.016

1.019

3351

3440

3538

3658

3800

3951

4113

4322

4584

0.991

1.026

4932

4916

4899

4879

4856

4826

4792

4756

4685

1.064

0.935

540

538

537

535

533

530

527

523

516

1.045

0.952

MAX ENDURANCE

332

346

356

370

384

397

413

427

455

1.045

0.953

2085

2304

2539

2788

3037

3284

3545

3844

4146

1.048

0.950

MAX RANGE

395

428

432

451

465

473

473

480

490

1.045

0.953

2261

2588

2760

3049

3311

3538

3725

3993

4325

1.048

0.950

Figure B43.(Sheet 43)

DRA

G INDEX=200

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

22

24

26

28

30

32

34

36

38

40

44

48

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=250

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

B450Change 3

Subsonic Cruise   35,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-54

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

3043

3162

3286

3424

3590

3776

1.055

0.948

272

296

319

344

372

403

1.044

0.955

2622

3073

1.136

0.901

2437

2760

3139

1.095

0.918

2448

2674

2946

3276

1.074

0.949

2575

2764

2973

3200

3473

1.043

0.960

2754

2917

3102

3302

3519

3788

1.033

0.977

3022

3155

3302

3477

3667

3899

1.023

1.001

3360

3480

3612

3755

3914

4134

1.004

1.031

3843

3941

4062

4214

4394

4587

0.979

1.041

4813

4799

4782

4758

4730

4657

1.066

0.935

529

527

526

523

520

513

1.045

0.952

MAX ENDURANCE

338

352

367

381

394

406

1.045

0.953

2412

2666

2928

3188

3457

3761

1.048

0.950

MAX RANGE

413

430

441

461

462

473

1.045

0.953

2709

2980

3233

3558

3746

4050

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

3060

3183

3323

3481

3680

1.055

0.950

276

300

326

354

387

1.043

0.954

2709

1.108

0.909

2545

2869

3271

1.092

0.923

2579

2808

3079

3439

1.069

0.954

2742

2931

3138

3362

3667

1.038

0.967

2967

3130

3313

3512

3758

1.023

0.986

3282

3415

3561

3739

3963

1.012

1.012

3672

3792

3926

4097

4286

0.996

1.051

4261

4376

4518

0.956

1.067

4735

4722

4687

4594

4447

1.069

0.931

521

520

516

506

490

1.047

0.948

MAX ENDURANCE

337

351

366

380

393

1.045

0.953

2525

2792

3066

3341

3655

1.048

0.950

MAX RANGE

394

418

430

445

458

1.045

0.953

2772

3117

3388

3695

4030

1.048

0.950

Figure B43.(Sheet 44)

DRA

G INDEX=300

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

22

24

26

28

30

32

34

36

38

40

44

48

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=350

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

Change 3B451

Subsonic Cruise   35,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-54

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

3210

3366

3564

1.055

0.949

305

334

368

1.043

0.954

2978

1.092

0.927

2942

3212

1.065

0.960

3099

3303

3554

1.033

0.972

3342

3524

3753

1.017

0.992

3674

3839

4045

1.001

1.024

4140

4298

0.982

1.037

4514

4408

4223

1.073

0.923

498

486

465

1.049

0.941

MAX ENDURANCE

351

365

379

1.045

0.953

2917

3203

3522

1.048

0.950

MAX RANGE

403

414

425

1.045

0.953

3198

3475

3794

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

3426

1.055

0.949

345

1.043

0.956

3369

1.072

0.949

3487

1.028

0.981

3769

1.007

1.003

4082

1.068

0.922

445

1.050

0.940

MAX ENDURANCE

365

1.045

0.953

3358

1.048

0.950

MAX RANGE

403

1.045

0.953

3597

1.048

0.950

Figure B43.(Sheet 45)

DRA

G INDEX=400

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

22

24

26

28

30

32

34

36

38

40

44

48

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

T.O. GR1F16CJ11

B452Change 3

Subsonic Cruise   35,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-54

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

3528

1.055

0.946

362

1.042

0.958

3688

1.021

0.979

3721

1.066

0.926

394

1.053

0.935

MAX ENDURANCE

365

1.045

0.953

3524

1.048

0.950

MAX RANGE

393

1.045

0.953

3718

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

Figure B43.(Sheet 46)

DRA

G INDEX=0

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

20

22

24

26

28

30

32

34

36

38

40

42

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=50

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

Change 3B453

Subsonic Cruise   40,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-56

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2515

2617

2718

2841

2963

3104

3256

3423

1.057

0.950

295

320

345

370

395

420

445

469

1.044

0.954

2427

1.152

0.856

2051

2442

1.136

0.886

1875

2176

2521

1.111

0.906

1816

2051

2317

2627

1.094

0.922

1812

2006

2230

2474

2750

1.074

0.916

1869

2023

2203

2406

2641

2894

3211

1.073

0.926

1969

2095

2237

2403

2600

2822

3069

3362

1.059

0.939

2032

2142

2273

2415

2593

2816

3053

3312

1.057

1.109

2576

2677

2819

2980

3154

3348

3595

3880

0.875

1.202

4005

4154

0.729

1.283

4268

4225

4194

4158

4118

4077

4032

3975

1.068

0.932

576

571

568

564

560

555

551

544

1.045

0.951

MAX ENDURANCE

407

428

445

468

483

488

500

502

1.045

0.953

1805

2004

2203

2396

2600

2812

3050

3301

1.048

0.950

MAX RANGE

515

516

516

516

516

516

516

516

1.045

0.953

2050

2159

2281

2414

2572

2804

3051

3315

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2530

2634

2750

2881

3023

3188

3387

3724

1.058

0.949

299

324

351

378

406

434

464

508

1.044

0.954

2512

1.154

0.857

2138

2548

1.135

0.892

1975

2283

2642

1.105

0.912

1948

2179

2444

2768

1.087

0.933

1974

2170

2390

2631

2919

1.064

0.929

2059

2217

2401

2608

2842

3113

1.055

0.942

2197

2321

2466

2653

2856

3079

3360

1.042

0.957

2315

2437

2572

2739

2947

3177

3431

3733

1.034

1.151

3121

3244

3398

3567

3766

0.823

1.261

4096

4073

4047

4016

3985

3946

3885

3789

1.071

0.932

557

555

552

549

545

539

529

517

1.045

0.951

MAX ENDURANCE

393

413

431

452

461

470

488

508

1.045

0.953

1948

2168

2386

2608

2835

3075

3353

3724

1.048

0.950

MAX RANGE

512

516

516

516

516

516

516

516

1.045

0.953

2326

2456

2585

2757

2962

3203

3467

3769

1.048

0.950

Figure B43.(Sheet 47)

DRA

G INDEX=100

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

20

22

24

26

28

30

32

34

36

38

42

46

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=150

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

B454Change 3

Subsonic Cruise   40,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-56

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2545

2656

2787

2933

3105

3345

1.057

0.950

303

330

359

389

421

458

1.044

0.953

2226

1.114

0.905

2077

2389

2773

1.099

0.918

2080

2308

2571

2925

1.081

0.943

2140

2334

2550

2788

1.050

0.947

2253

2417

2604

2810

3052

1.039

0.957

2421

2559

2718

2907

3111

3368

1.028

0.978

2615

2759

2916

3086

3301

3563

1.006

0.996

3714

3846

0.778

1.118

3983

3966

3944

3918

3884

3822

1.066

0.925

545

542

538

534

528

521

1.046

0.951

MAX ENDURANCE

372

392

407

425

453

459

1.045

0.953

2070

2308

2546

2787

3052

3345

1.048

0.950

MAX RANGE

448

470

485

488

488

488

1.045

0.953

2243

2501

2745

2944

3145

3391

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2561

2684

2832

3003

3295

1.057

0.951

307

337

368

403

451

1.044

0.953

2313

1.113

0.911

2183

2496

1.086

0.936

2211

2437

2698

1.061

0.956

2305

2497

2711

2967

1.042

0.960

2455

2620

2807

3016

1.026

0.970

2670

2811

2971

3161

3404

1.016

0.997

2954

3101

3260

3443

3693

0.985

1.020

3911

3894

3863

3828

3785

1.062

0.921

532

530

526

522

516

1.046

0.951

MAX ENDURANCE

363

380

397

418

451

1.045

0.953

2181

2433

2682

2967

3295

1.048

0.950

MAX RANGE

441

464

470

473

487

1.045

0.953

2404

2694

2906

3116

3453

1.048

0.950

Figure B43.(Sheet 48)

DRA

G INDEX=200

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

22

24

26

28

30

32

34

36

38

40

44

48

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=250

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

Change 3B455

Subsonic Cruise   40,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-56

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2717

2894

3206

1.057

0.950

344

381

437

1.043

0.954

2611

1.097

0.925

2566

2851

1.078

0.960

2660

2878

1.035

0.971

2823

3013

3260

1.024

0.975

3063

3235

3462

1.005

1.015

3453

3637

0.964

1.045

3816

3788

3613

1.062

0.919

520

517

494

1.046

0.949

MAX ENDURANCE

379

395

437

1.045

0.953

2551

2833

3206

1.048

0.950

MAX RANGE

447

463

470

1.045

0.953

2803

3094

3374

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2766

3012

1.056

0.950

355

405

1.043

0.954

2739

1.079

0.922

2695

1.054

0.972

2823

3073

1.029

0.982

3033

3258

1.010

0.991

3342

0.986

1.007

3671

3444

1.060

0.909

502

472

1.047

0.941

MAX ENDURANCE

378

405

1.045

0.953

2675

3012

1.048

0.950

MAX RANGE

430

445

1.045

0.953

2882

3223

1.048

0.950

Figure B43.(Sheet 49)

DRA

G INDEX=0

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

20

22

24

26

28

30

32

34

36

38

40

42

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=50

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

B456Change 3

Subsonic Cruise   45,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-56

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2256

2380

2525

2685

2880

1.059

0.947

364

396

428

459

492

1.044

0.954

2049

1.113

0.909

1944

2218

1.097

0.926

1901

2135

2394

1.079

0.933

1911

2107

2335

2596

1.071

0.950

1954

2124

2343

2581

2874

1.051

1.078

2412

2583

2784

3048

0.886

1.160

3376

3336

3294

3243

3119

1.057

0.928

565

559

554

547

529

1.045

0.952

MAX ENDURANCE

459

480

488

502

502

1.045

0.953

1898

2107

2325

2573

2865

1.048

0.950

MAX RANGE

516

516

516

516

516

1.045

0.953

1965

2124

2347

2589

2879

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2286

2429

2603

2837

1.058

0.947

371

407

443

485

1.044

0.954

2152

1.113

0.916

2070

2355

1.093

0.937

2063

2295

2579

1.067

0.945

2108

2310

2540

1.050

0.970

2201

2396

2623

2894

1.028

1.136

2868

3063

0.830

1.236

3261

3229

3162

3071

1.058

0.931

549

545

535

522

1.046

0.951

MAX ENDURANCE

442

459

476

488

1.045

0.953

2060

2291

2539

2835

1.048

0.950

MAX RANGE

510

516

516

516

1.045

0.953

2200

2417

2649

2926

1.048

0.950

Figure B43.(Sheet 50)

DRA

G INDEX=100

TOTAL FUEL FLOW LB/HR

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

20

22

24

26

28

30

32

34

36

38

42

46

EFFECT FACTOR

TEMP

+20C -20C

°

°

KTAS

GW-

1000

LB

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

*

DRA

G INDEX=150

MIL

VMIN

MIL

VMAX

KTAS

FUEL FLOW

KTAS

FUEL FLOW

180

210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660

T.O. GR1F16CJ11

Change 3B457

Subsonic Cruise   45,000 Feet

DATA BASIS FLIGHT TEST

CONDITIONS:

ENGINE F110GE129

STANDARD DAY TEMPERATURE (-56

°

C)

NOTE:

REFER TO SECTION V FOR AIRSPEED LIMITATIONS.

2324

2496

2769

1.058

0.948

381

422

474

1.044

0.955

2273

1.083

0.915

2196

1.067

0.952

2224

2463

1.052

0.963

2309

2513

2779

1.039

0.986

2467

2667

2933

1.011

0.999

3156

3112

3047

1.059

0.932

535

528

518

1.046

0.951

MAX ENDURANCE

419

451

474

1.045

0.953

2196

2463

2769

1.048

0.950

MAX RANGE

488

488

493

1.045

0.953

2339

2542

2820

1.048

0.950

*TEMPERATURE DEVIATION FROM STANDARD DAY.

2375

2662

1.057

0.949

394

455

1.043

0.955

2331

1.063

0.957

2386

1.039

0.977

2511

2745

1.024

1.002

2736

2976

0.993

1.017

3076

3023

1.059

0.932

522

514

1.045

0.951

MAX ENDURANCE

411

455

1.045

0.953

2329

2662

1.048

0.950

MAX RANGE

470

487

1.045

0.953

2459

2785

1.048

0.950

Figure B43.(Sheet 51)

T.O. GR1F16CJ11

B458Change 3

Diversion Decision Divert

DATA BASIS FLIGHT TEST

ENGINE F110GE129

CONDITIONS:

MIL CLIMB AT 433 KIAS OR OPTIMUM

ALTITUDE MACH NUMBER, WHICHEVER IS LESS

DESCEND AT IDLE, 221 KIAS

STANDARD DAY

NO FUEL RESERVE

ZERO WIND

ALL DESCENTS ARE TO SEA LEVEL

DRAG INDEX = 55

IF YOU ARE AT SEA LEVEL

FUEL ON

REMAIN

AT SEA LEVEL

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT SEA LEVEL

TOTAL DIVERT

FROM

FUEL USED

BOARD

 LB

TOTAL DIVERT

RANGE NM

ALT/MACH

TOTAL DIVERT

RANGE

 NM

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

20

10.0K/0.50

20

16

70

400

38

20.0K/0.60

49

33

127

600

57

30.0K/0.70

83

53

184

800

76

0.44M

35.0K/0.75

120

64

215

1000

94

35.0K/0.75

158

64

215

1500

141

45.0K/0.90

258

98

304

2000

187

45.0K/0.90

357

98

304

IF YOU ARE AT 5000 FEET

FUEL ON

REMAIN

AT 5000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 5000 FT

TOTAL DIVERT

FROM

FUEL USED

BOARD

 LB

TOTAL DIVERT

RANGE NM*

ALT/MACH

TOTAL DIVERT

RANGE

 NM

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

26

10.0K/0.50

26

16

70

400

47

25.0K/0.66

57

43

157

600

68

30.0K/0.70

93

53

184

800

89

0.46M

35.0K/0.75

131

64

215

1000

110

35.0K/0.75

169

64

215

1500

162

45.0K/0.90

270

98

304

2000

213

45.0K/0.90

369

98

304

*

 START DESCENT AT 9 NM. 41 LB FUEL USED IN DESCENT.

IF YOU ARE AT 10,000 FEET

FUEL ON

REMAIN

AT 10 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 10,000 FT

TOTAL DIVERT

FROM

FUEL USED

BOARD

 LB

TOTAL DIVERT

RANGE NM*

ALT/MACH

TOTAL DIVERT

RANGE

 NM

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

32

15.0K/0.53

32

24

97

400

56

25.0K/0.66

64

43

157

600

79

35.0K/0.75

103

64

215

800

103

0.50M

35.0K/0.75

141

64

215

1000

126

40.0K/0.90

181

83

265

1500

184

45.0K/0.90

282

98

304

2000

242

40.0K/0.90

382

83

265

*

 START DESCENT AT 16 NM. 70 LB FUEL USED IN DESCENT.

NOTES:

4.0% RANGE GAIN FOR 10 KNOTS TAILWIND.

2.5% RANGE LOSS FOR 10 KNOTS HEADWIND.

SUBTRACT 2.0 NM FROM DESCENT DISTANCE FOR EACH 1000 FT OF DESTINATION ELEVATION.

TOTAL DIVERT RANGE AT CURRENT ALTITUDE INCLUDES CRUISE AND DESCENT, AND TOTAL DIVERT

RANGE AT OPTIMUM ALTITUDE INCLUDES CLIMB, CRUISE, AND DESCENT.

Figure B44.(Sheet 1)

T.O. GR1F16CJ11

Change 3B459

Diversion Decision Divert

DATA BASIS FLIGHT TEST

ENGINE F110GE129

CONDITIONS:

MIL CLIMB AT 433 KIAS OR OPTIMUM

ALTITUDE MACH NUMBER, WHICHEVER IS LESS

DESCEND AT IDLE, 221 KIAS

STANDARD DAY

NO FUEL RESERVE

ZERO WIND

ALL DESCENTS ARE TO SEA LEVEL

DRAG INDEX = 55

IF YOU ARE AT 20,000 FEET

FUEL ON

REMAIN

AT 20 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 20,000 FT

TOTAL DIVERT

FROM

FUEL USED

BOARD

 LB

TOTAL DIVERT

RANGE NM*

ALT/MACH

TOTAL DIVERT

RANGE

 NM

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

44

20.0K/0.60

44

33

127

400

74

35.0K/0.75

80

64

215

600

103

40.0K/0.90

123

83

265

800

132

0.60M

40.0K/0.90

164

83

265

1000

161

45.0K/0.90

205

98

304

1500

233

45.0K/0.90

307

98

304

2000

305

40.0K/0.90

406

83

265

*

 START DESCENT AT 33 NM. 126 LB FUEL USED IN DESCENT.

IF YOU ARE AT 30,000 FEET

FUEL ON

REMAIN

AT 30 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 30,000 FT

TOTAL DIVERT

FROM

FUEL USED

BOARD

 LB

TOTAL DIVERT

RANGE NM*

ALT/MACH

TOTAL DIVERT

RANGE

 NM

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

56

30.0K/0.70

56

53

184

400

92

35.0K/0.75

94

64

215

600

128

40.0K/0.90

139

83

265

800

163

0.70M

45.0K/0.90

180

98

304

1000

199

45.0K/0.90

221

98

304

1500

287

45.0K/0.90

322

98

304

2000

374

40.0K/0.90

422

83

265

*

 START DESCENT AT 53 NM. 183 LB FUEL USED IN DESCENT.

IF YOU ARE AT 40,000 FEET

FUEL ON

REMAIN

AT 40 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 40,000 FT

TOTAL DIVERT

FROM

FUEL USED

BOARD

 LB

TOTAL DIVERT

RANGE NM*

ALT/MACH

TOTAL DIVERT

RANGE

 NM

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

111

40.0K/0.90

111

83

265

600

153

40.0K/0.90

153

83

265

800

194

0.90M

45.0K/0.90

194

98

304

1000

235

45.0K/0.90

235

98

304

1500

336

45.0K/0.90

336

98

304

2000

436

40.0K/0.90

436

83

265

* 

START DESCENT AT 83 NM. 265 LB FUEL USED IN DESCENT.

NOTES:

4.0% RANGE GAIN FOR 10 KNOTS TAILWIND.

2.5% RANGE LOSS FOR 10 KNOTS HEADWIND.

SUBTRACT 2.0 NM FROM DESCENT DISTANCE FOR EACH 1000 FT OF DESTINATION ELEVATION.

TOTAL DIVERT RANGE AT CURRENT ALTITUDE INCLUDES CRUISE AND DESCENT, AND TOTAL DIVERT

RANGE AT OPTIMUM ALTITUDE INCLUDES CLIMB, CRUISE, AND DESCENT.

Figure B44.(Sheet 2)

T.O. GR1F16CJ11

B460Change 3

Diversion Decision Loiter

DATA BASIS FLIGHT TEST

ENGINE F110GE129

CONDITIONS:

MIL CLIMB AT 433 KIAS OR OPTIMUM

ALTITUDE MACH NUMBER, WHICHEVER IS LESS

DESCEND AT IDLE, 221 KIAS

STANDARD DAY

NO FUEL RESERVE

ZERO WIND

ALL DESCENTS ARE TO SEA LEVEL

DRAG INDEX = 55

IF YOU ARE AT SEA LEVEL

FUEL ON

REMAIN

AT SEA LEVEL

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT SEA LEVEL

FROM

FUEL USED

BOARD

 LB

TOTAL LOITER

TIME MIN

ALT/MACH

TOTAL TIME

 MIN

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

9

0.0K/0.31

9

0

0

600

13

15.0K/0.42

14

21

89

800

18

0.32M

30.0K/0.58

21

50

176

1000

22

35.0K/0.64

26

60

204

1500

32

30.0K/0.59

39

50

176

2000

42

30.0K/0.60

51

50

176

IF YOU ARE AT 5000 FEET

FUEL ON

REMAIN

AT 5000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 5000 FT

FROM

FUEL USED

BOARD

 LB

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

 MIN

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

11

5.0K/0.35

11

7

34

600

15

20.0K/0.46

16

30

116

800

20

0.35M

30.0K/0.58

22

50

176

1000

24

35.0K/0.65

27

60

204

1500

35

30.0K/0.59

40

50

176

2000

46

30.0K/0.60

52

50

176

*

 START DESCENT AT 7 NM. 34 LB FUEL USED IN DESCENT.

IF YOU ARE AT 10,000 FEET

FUEL ON

REMAIN

AT 10 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 10,000 FT

FROM

FUEL USED

BOARD

 LB

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

 MIN

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

12

10.0K/0.38

12

14

63

600

17

25.0K/0.51

17

39

146

800

22

0.39M

35.0K/0.64

23

60

204

1000

26

30.0K/0.59

28

50

176

1500

38

30.0K/0.59

41

50

176

2000

49

30.0K/0.60

53

50

176

*

 START DESCENT AT 14 NM. 63 LB FUEL USED IN DESCENT.

NOTES:

LOITER TIME AT CONSTANT ALTITUDE BASED ON 10 NM HOLDING PATTERN WITH 30DEGREE BANK

TURNS.

ADD 0.4 MIN TO LOITER TIME FOR EACH 1000 FT OF DESTINATION ELEVATION.

SUBTRACT 1.7 NM FROM DESCENT DISTANCE FOR EACH 1000 FT OF DESTINATION ELEVATION.

TOTAL LOITER TIME AT CURRENT ALTITUDE INCLUDES LOITER AND DESCENT, AND TOTAL TIME AT

OPTIMUM ALTITUDE INCLUDES CLIMB, LOITER, AND DESCENT.

Figure B44.(Sheet 3)

T.O. GR1F16CJ11

Change 3B461

Diversion Decision Loiter

DATA BASIS FLIGHT TEST

ENGINE F110GE129

CONDITIONS:

MIL CLIMB AT 433 KIAS OR OPTIMUM

ALTITUDE MACH NUMBER, WHICHEVER IS LESS

DESCEND AT IDLE, 221 KIAS

STANDARD DAY

NO FUEL RESERVE

ZERO WIND

ALL DESCENTS ARE TO SEA LEVEL

DRAG INDEX = 55

IF YOU ARE AT 20,000 FEET

FUEL ON

REMAIN

AT 20 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 20,000 FT

FROM

FUEL USED

BOARD

 LB

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

 MIN

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

14

20.0K/0.46

14

30

116

600

20

30.0K/0.58

20

50

176

800

25

0.47M

30.0K/0.59

25

50

176

1000

30

30.0K/0.59

30

50

176

1500

42

30.0K/0.59

43

50

176

2000

53

30.0K/0.60

55

50

176

*

 START DESCENT AT 30 NM. 116 LB FUEL USED IN DESCENT.

IF YOU ARE AT 30,000 FEET

FUEL ON

REMAIN

AT 30 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 30,000 FT

FROM

FUEL USED

BOARD

 LB

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

 MIN

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

 

 

 

 

 

600

22

30.0K/0.58

22

50

176

800

27

0.59M

30.0K/0.59

27

50

176

1000

32

30.0K/0.59

32

50

176

1500

45

30.0K/0.60

45

50

176

2000

56

30.0K/0.60

56

50

176

*

 START DESCENT AT 49 NM. 175 LB FUEL USED IN DESCENT.

IF YOU ARE AT 40,000 FEET

FUEL ON

REMAIN

AT 40 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 40,000 FT

FROM

FUEL USED

BOARD

 LB

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

 MIN

FROM

OPT ALT

 NM

FUEL USED

IN DESCENT

 LB

200

 

 

 

 

 

400

 

 

 

 

 

600

23

40.0K/0.72

23

75

245

800

28

0.73M

40.0K/0.72

28

75

245

1000

33

40.0K/0.73

33

75

245

1500

44

40.0K/0.74

44

75

245

2000

55

40.0K/0.75

55

75

245

* 

START DESCENT AT 75 NM. 244 LB FUEL USED IN DESCENT.

NOTES:

LOITER TIME AT CONSTANT ALTITUDE BASED ON 10 NM HOLDING PATTERN WITH 30DEGREE BANK

TURNS.

ADD 0.4 MIN TO LOITER TIME FOR EACH 1000 FT OF DESTINATION ELEVATION.

SUBTRACT 1.7 NM FROM DESCENT DISTANCE FOR EACH 1000 FT OF DESTINATION ELEVATION.

TOTAL LOITER TIME AT CURRENT ALTITUDE INCLUDES LOITER AND DESCENT, AND TOTAL TIME AT

OPTIMUM ALTITUDE INCLUDES CLIMB, LOITER, AND DESCENT.

Figure B44.(Sheet 4)

 

 

 

 

 

 

 

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