Exhibit_5.pdf

R 011456Z JUL 10

FM COMDT COGARD WASHINGTON DC//711//

TO AIG 4907

BT

UNCLAS //N13011//

SUBJ: CHANGE 9, CHANGE 10, AND TOPS 8 TO CGTO 1C-130H-1-1 C-130H FLIGHT

(PERFORMANCE) MANUAL

A. FLIGHT (PERFORMANCE) MANUAL C-130H SERIES AIRCRAFT, CGTO1C-130H-1-1

B. TECHNICAL ORDER PAGE SUPPLEMENT EIGHT, CGTO 1C-130H-1-1 TP-8

1. INCORPORATE CHANGE 9, CHANGE 10, AND TOPS 8 INTO REF A.

2. CHANGE 9 TO REF A, EFFECTIVE 04 FEBRUARY 2009, REMOVES TACTICALTAKEOFF

PROCEDURES FROM SECTION 3. THE USCG HAS CHOSEN TO RETAINTACTICAL

PROCEDURES, AND HAS INCOPORATED TACTICAL PROCEDURES INTOTOPS 8.

EFFECTIVELY, USCG PROCEDURES REMAIN UNCHANGED REGARDINGTACTICAL

TAKEOFF.

3. CHANGE 10 TO REF A, EFFECTIVE 19 FEB 2010, HAS NO SIGNIFICANTIMPACT TO

USCG OPERATIONS. CHANGE 10 REVISES REFERENCES AND CHARTCORRECTIONS

FOR DER (DEPARTURE END OF RUNWAY).

4. TOPS 8 AUGMENTS TOPS 7, REPLACING FIVE OF TWELVE TOPS 7 PAGES.TOPS 8

INCORPORATES TACTICAL PROCEDURES, AND MAKES MINOR CORRECTIONSTO TOPS

7 ASSAULT PROCEDURES, NWS PROCEDURES, AND TOLD PROCEDURES.

5. ELECTRONIC COPIES OF CHANGE 9, CHANGE 10, AND TOPS 8 WILL BEAVAILABLE

VIA THE ALC WEBSITE.

6. ATC POINTS OF CONTACT ARE LCDR JOE BOYES (727) 535-1437 EXT 2110,AND

AMTC ROBERT FIELDER, EXT 2115.

BT

P 221924Z FEB 10 ZUI ASN-AM1053000137

FM COMDT COGARD WASHINGTON DC//CG-711//

TO COGARD AIRSTA BARBERS PT HI//130 ENG/OPS//

COGARD AIRSTA KODIAK AK//130 ENG/OPS//

COGARD AIRSTA CLEARWATER FL//130 ENG/OPS//

COGARD AIRSTA SACRAMENTO CA//ENG/OPS//

COGARD ATC MOBILE AL//130 STAN//

COGARD ALC ELIZABETH CITY NC//LRS//

BT

UNCLAS //N13011//

SUBJ: CHANGES 8, 9 AND 10 TO THE C-130H SERIES FLIGHT

(PERFORMANCE) MANUAL

A. FLIGHT (PERFORMANCE) MANUAL C-130H SERIES AIRCRAFT, CGTO

1C-130H-1-1

1. CHANGE 8 TO REF A, EFFECTIVE 15 DEC 2009, HAS BEEN RELEASED TO

THE C-130H FLEET AND DOES NOT AFFECT CURRENT USCG OPERATIONS.

SOME HIGHLIGHTS INCLUDE:

A. SPECIFIES RCR EQUAL TO 23 REQUIRED TO CALCULATE TAKEOFF

DATA USING THE WITH NOSEWHEEL STEERING OPTION.

B. TO ALIGN WITH ICAO BRAKING CATEGORIES, FAIR EQUATES TO

RCR OF 12 AND POOR/NIL EQUATES TO RCR OF 5.

C. MOVES TABULAR DATA FOR CRITICAL ENGINE FAILURE SPEED

COMPARISONS FROM PAGE 3-18 TO 3-36.1.

D. ADDS CHARTS FOR RCR EQUAL TO 2 FOR REFUSAL SPEED

CALCULATIONS.

2. CHANGE 9 TO REF A WAS APPROVED BY THE USAF EFFECTIVE 04 FEB

2010 AND WILL BE FORWARDED TO USCG UNITS IN THE NEAR FUTURE.

USCG UNITS ARE DIRECTED TO NOT IMPLEMENT CHANGE 9 UNTIL

FURTHER GUIDANCE IS PROVIDED BY THE C-130H STAN TEAM AND CG-711

VIA SEPCOR.

3. CHANGE 10 HAS BEEN FINALIZED AND IS AWAITING USAF APPROVAL.

LIKE CHANGE 9, USCG C-130H UNITS ARE DIRECTED TO NOT IMPLEMENT

CHANGE 10 UNTIL FURTHER GUIDANCE IS ISSUED BY THE C-130H STAN

TEAM AND CG-711.

4. C-130H STAN TEAM POCS ARE LCDR JOE BOYES (727) 535-1437 EXT 2110,

AND AMTC ROBERT FIELDER, EXT 2115.

BT

NNNN

CGTO 1C-130H-1-1TP-9

TECHNICAL ORDER PAGE SUPPLEMENT

FLIGHT MANUAL

USCG SERIES

C-130H AIRPLANES

EQUIPPED WITH T56-A-15 ENGINES

THIS TOPS SUPPLEMENTS CGTO 1C-130H-1-1 DATED 25 JULY 2012.

THIS TOPS SUPERSEDES PAGE 1-6 FROM CGTO 1C-130H-1-1TP-7. REMOVE AND DESTROY PAGE 1-6

FROM TP-7 AND REPLACE WITH PAGE FROM CGTO 1C-130H-1-1TP-9.

PUBLISHED UNDER THE AUTHORITY OF THE COMMANDANT OF THE U.S. COAST GUARD AND

UNDER THE DIRECTION OF THE CHIEF, OFFICE OF ENGINEERING, U.S. COAST GUARD.

DISTRIBUTION STATEMENT D: Distribution authorized to the DHS/CG/DoD and their contractors, Administrative or Operational Use;

26 December 2013. Other requests shall be referred to Aviation Logistics Center (ALC) Medium Range Recovery (MRR) Technical Services.

WARNING: This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et.

Seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et. Seq. Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

DESTRUCTION NOTICE: For classified documents, follow the procedures in DoD 5200.22-M, National Industrial Security Program Operating Manual, Section 5-705 or DoD 5200.1-R, information Security Program Regulation, Chapter VI, Section 7. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

26 December 2013

LIST OF EFFECTIVE PAGES

NOTE: This Coast Guard TOPS contains supplementary information. Text pages do not supersede pages of the basic TO but will be inserted facing the amended page. Total number of TOPS pages in CGTO 1C-130H-1-1TP-9 is 2.

PAGE NO. TOPS PAGE NO. TOPS

*Title Page TP-9

Page 1-1 TP-8

*Page 1-6 TP-9

Page 3-17 TP-8

Page 3-24 TP-7

Page 3-36.2 TP-8

Page 3-57 TP-7

Page 6A-11 TP-7

Page 10-1 TP-7

Page 10-2 TP-8

Page 10-8 TP-7

Page 10-9 TP-7

*Denotes pages included in this TOPS.

CGTO 1C--130H--1--1 TP--8

TECHNICAL ORDER PAGE SUPPLEMENT

FLIGHT MANUAL

USAF SERIES

C--130 AIRPLANES

EQUIPPED WITH T56--A--15 ENGINES

THIS TOPS SUPPLEMENTS USAF TO 1C--130H--1--1 DATED 15 MARCH 2001, THROUGH

CHANGE NO. 10 DATED 19 FEBRUARY 2010.

NOTE: IF AFTO 1C--130H--1--1 IS REVISED, DO NOT DISPOSE OF TOPS BEFORE CONTACTING ALC

TECHNICAL PUBLICATIONS BRANCH, ELIZABETH CITY, NC, AND THE C--130H

STANDARDIZATION TEAM, CLEARWATER, FL.

THIS TOPS SUPERSEDES PAGES 1--1, 3--36.2, AND 10--2 FROM CGTO 1C--130H--1--1 TP--7. REMOVE AND DESTROY PAGES 1--1, 3--36.2, AND 10--2 FROM TP--7 AND REPLACE WITH PAGES FROM CGTO

1C--130H--1--1 TP--8.

PUBLISHED UNDER THE AUTHORITY OF THE COMMANDANT OF THE U.S. COAST GUARD AND

UNDER THE DIRECTION OF THE CHIEF, OFFICE OF ENGINEERING, U.S. COAST GUARD

DISTRIBUTION STATEMENT D: Distribution authorized to the DHS/CG/DoD and their contractors Administrative/Operational Use, 3 May 2010. Other requests shall be referred to Aviation Logistics Center (ALC) Long Range Surveillance (HC--130H) Technical Services.

WARNING: This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751,

et. seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C. App. 2401 et. seq. Violations of these export laws are sub-ject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

DESTRUCTION NOTICE: For classified documents, follow the procedures in DoD 5200.22--M, National Industrial Security Program Operating Manual, Section 5--705 or DoD 5200.1--R, Information Security Program Regulation, Chapter VI, Section 7. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

3 May 2010

LIST OF EFFECTIVE PAGES

NOTE: This Coast Guard TOPS contains supplementary information. Text pages do not supersede pages of the basic TO but will be inserted facing the amended page. This TOPS was generated by CG MSG P221924Z FEB 10. Total number of pages in CGTO 1C--130H--1--1 TP--8 is 5.

PAGE NO. TOPS PAGE NO. TOPS

*Title Page TP--8 Page 3--57 TP--7

*Page 1--1 TP--8 Page 6A--11 TP--7

Page 1--6 TP--7 Page 10--1 TP--7

*Page 3--17 TP--8 *Page 10--2 TP--8

Page 3--24 TP--7 Page 10--8 TP--7

*Page 3--36.2 TP--8 Page 10--9 TP--7

* Denotes pages included in this TOPS.

CGTO 1C--130H--1--1 TP--7

TECHNICAL ORDER PAGE SUPPLEMENT

FLIGHT MANUAL

USAF SERIES

C--130 AIRPLANES

EQUIPPED WITH T56--A--15 ENGINES

THIS TOPS SUPPLEMENTS USAF TO 1C--130H--1--1 DATED 15 MARCH 2001,

CHANGE NO. 8 DATED 15 DECEMBER 2009.

NOTE: IF AFTO 1C--130H--1--1 IS REVISED, DO NOT DISPOSE OF TOPS BEFORE CONTACTING ALC

TECHNICAL PUBLICATIONS BRANCH, ELIZABETH CITY, NC, AND THE C--130H

STANDARDIZATION TEAM, CLEARWATER, FL.

THIS TOPS SUPERSEDES CGTO 1C--130H--1--1 TP--6. REMOVE AND DESTROY CG TOPS NUMBER 6 AND

REPLACE WITH CGTO 1C--130H--1--1 TP--7. TP--7 IS THE ONLY ACTIVE TOPS.

PUBLISHED UNDER THE AUTHORITY OF THE COMMANDANT OF THE U.S. COAST GUARD AND

UNDER THE DIRECTION OF THE CHIEF, OFFICE OF ENGINEERING, U.S. COAST GUARD

DISTRIBUTION STATEMENT D: Distribution authorized to the DHS/CG/DoD and their contractors Administrative/Operational Use, 10 February 2010. Other requests shall be referred to Aviation Logistics Center (ALC) Long Range Surveillance (HC--130H) Technical Services.

WARNING: This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751,

et. seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C. App. 2401 et. seq. Violations of these export laws are sub-ject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

DESTRUCTION NOTICE: For classified documents, follow the procedures in DoD 5200.22--M, National Industrial Security Program Operating Manual, Section 5--705 or DoD 5200.1--R, Information Security Program Regulation, Chapter VI, Section 7. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

10 Feb 2010

LIST OF EFFECTIVE PAGES

NOTE: This Coast Guard TOPS contains supplementary information. Text pages do not supersede pages of the basic TO but will be inserted facing the amended page. This TOPS was generated by CG MSG R031813ZJUL07ZUIASN--A00184000036 and Change 8 dated 15 December 2009. Total number of pages in CGTO 1C--130H--1--1 TP--7 is 11.

PAGE NO. TOPS PAGE NO. TOPS

Title Page TP--7 Page 6A--11 TP--7

Page 1--1 TP--7 Page 10--1 TP--7

Page 1--6 TP--7 Page 10--2 TP--7

Page 3--24 TP--7 Page 10--8 TP--7

Page 3--36.2 TP--7 Page 10--9 TP--7

Page 3--57 TP--7

CGTO 1C-130H-1-1

25 JULY 2012

FLIGHT MANUAL

U.S. COAST GUARD

SERIES HC-130H AIRCRAFT

PERFORMANCE DATA

COMMANDING OFFICERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION

TO THE ATTENTION OF ALL AFFECTED PERSONNEL

PUBLISHED UNDER THE AUTHORITY OF THE COMMANDANT OF THE

U.S. COAST GUARD

THIS PUBLICATION IS INCOMPLETE WITHOUT THE APPLICABLE VERSION OF

ENGINES 1C-130-1 FLIGHT MANUAL

Distribution Statement D: Distribution authorized to the DHS/CG/DoD and their contractors, for Administrative and Operational Use; 25 July 2012. Other requests shall be referred to Aviation Logistics Center (ALC) Long Range

Surveillance (HC-130H) Technical Services.

WARNING: This document contains technical data whose export is restricted by the Arms Export–Control Act

(Title 22, U.S.C., Sec 2751, et. seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App.

2401 et. seq. Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

DESTRUCTION NOTICE: For classified documents, follow the procedures in DoD 5200.22–M, National

Industrial Security Program Operating Manual, Section 5–705, or DoD 5200.1–R, Information Security Program

Regulation, Chapter VI, Section 7. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

RBRackley

TOPS 9

Flight Manual TO 1C-130H-1-1

THIS PUBLICATION ISUSAF SERIES INCOMPLETE WITHOUT

C-130 AIRPLANES The Applicable Version Of EQUIPPED WITH T56-A-15 ENGINES 1C-130-1 Flight Manual

PERFORMANCE DATA

F41608-78-G-0053 F09603-97-G-0011

COMMANDERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION TO THE ATTENTION OF ALL

AFFECTED PERSONNEL.

HANDLING AND DESTRUCTION NOTICE - Comply with distribution statement and destroy by any method that will prevent disclosure of the contents or reconstruction of the document.

PUBLISHED UNDER AUTHORITY OF THE SECRETARY OF THE AIR FORCE

15 MARCH 2001

CHANGE 10 - 19 FEBRUARY 2010

DISTRIBUTION STATEMENT – Distribution authorized to the Department of Defense and U.S. DoD contractors only (Administrative or Operational Use) (15 March 2001). Refer other requests for this document to WR-580 ACSG/GFEAH, Robins AFB, GA 31098.

WARNING – This document contains technical data whose export is restricted by the Arms ExportControl Act (Title 22, U.S.C., Sec. 2751 et seq.) or the Export Administration Act of 1979, as amended (Title 50, U.S.C., App. 2401 et seq.).

Violations of these export laws are subject to severe criminal penalties. Dissemination of this document is controlled under DoD Directive 5230.25.

REFER TO ETIMS OR THE AF TO CATALOG FOR CURRENT STATUS OF FLIGHT MANUALS, SAFETY SUPPLEMENTS, OPERATIONAL SUPPLEMENTS AND FLIGHT CREW CHECKLISTS.

THIS MANUAL IS A COMPLETE SET, BASIC THROUGH CHANGE 10.

TO 1C-130H-1-1

NOTE: The portion of the text affected by the changes is indicated by a vertical line in the margins of the page. Changes to illustrations are indicated by miniature pointing hands. Changes to wiring diagrams are indicated shaded areas.

INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.LIST OF EFFECTIVE PAGES

*Zero in this column indicates an original page.

Dates of issue for original and changed pages are:

Original . . . . . . . . . . . . . . . 0 . . . . . . . . . . 15 March 2001 Change . . . . . . . . . . . . . . . 1 . . . . . . . . . .31 January 2002 Change . . . . . . . . . . . . . . . 2 . . . . . . . . 15 December 2002 Change . . . . . . . . . . . . . . . 3 . . . . . . . . 17 November 2003 Change . . . . . . . . . . . . . . . 4 . . . . . . . . . . . . . 15 May 2005 Change . . . . . . . . . . . . . . . 5 . . . . . . . . . .16 October 2006

Change . . . . . . . . . . . . . . 6 . . . . . . . . . 31 January 2008 Change . . . . . . . . . . . . . . 7 . . . . . . . . . . . . . .6 July 2009 Change . . . . . . . . . . . . . . 8 . . . . . . . 15 December 2009 Change . . . . . . . . . . . . . . 9 . . . . . . . . . .4 February 2010 Change . . . . . . . . . . . . . . 10 . . . . . . . .19 February 2010

Page *Change No. No.

Page *Change No. No.

Page *Change No. No.

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 726 CONSISTING OF THE FOLLOWING:

A Change 10 USAF

Title A – C i ii Blank 1-1 1-2 1-3 – 1-5 1-6 1-7 1-8 1-9 – 1-10 1-10.1 – 1-10.2 1-11 1-12 – 1-13 1-14 1-15 –1-25 1-26 Blank 1A-1 – 1A-4 1A-5 1A-6 – 1A-7 1A-8 Blank 1B-1 1B-2 1B-3 – 1B-4 1B-5 1B-6 – 1B-7 1B-8 Blank 1C-1 – 1C-4 1C-5 1C-6 – 1C-7 1C-8 Blank 1D-1 – 1D-7 1D-8 Blank 1E-1 – 1E-4 1E-5 1E-6 – 1E-7 1E-8 Blank 2-1 – 2-3 2-4 – 2-5 2-6 2-7 2-8 2-9 2-10 Blank 3-1 3-2 – 3-4 3-5 3-6 3-7

3-8 3-9 3-10 3-11 3-12 3-12.1 3-12.2 Blank added 3-13 3-14 – 3-15 3-16 3-17 – 3-17.1 3-17.2 Added 3-18 3-19 – 3-21 3-22 3-23 3-24 – 3-25 3-26 3-27 3-28 3-29 3-30 – 3-32 3-33 – 3-34 3-35 3-36 3-36.1 3-36.2 3-37 – 3-42 3-43 – 3-44 3-45 – 3-47 3-48 3-49 – 3-50 3-51 3-52 – 3-54 3-55 3-56 3-57 3-57.1 – 3-57.2 3-58 – 3-61 3-62

3-62.1 DELETED

3-62.2 Blank DELETED 3-63 – 3-64 3-65 – 3-66 3-67 3-67.1 3-67.2 added 3-68 3-69 – 3-70

3-71 3-71.1 3-71.2 added 3-72 3-73 – 3-74 3-75 3-75.1 3-75.2 added 3-76 3-77 – 3-78 3-79 – 3-80 Deleted 3-81 3-82 – 3-86 3-87 3-88 – 3-99 3-100 3-101 – 3-109 3-110 3-111 – 3-119 3-120 Blank 3-121 – 3-124 3-125 – 3-142

3-143 – 3-144 DELETED

3-145 – 3-150 3-151 3-152 – 3-154 3-155 – 3-157 3-158 3-159 3-160 3-161 3-162 – 3-174 3-175 – 3-189 3-190 3-191 3-192 – 3-195 3-196 3-197 3-198 3-199 – 3-200 3-201 – 3-202 4-1 4-2 4-3 – 4-7 4-8 4-9 – 4-10 4-11 4-12 – 4-36 5-1 – 5-8

Page *Change No. No.

Page *Change No. No.

Page *Change No. No.

TO 1C-130H-1-1

NOTE: The portion of the text affected by the changes is indicated by a vertical line in the margins of the page. Changes to illustrations are indicated by miniature pointing hands. Changes to wiring diagrams are indicated by shaded areas.

INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDEDLIST OF EFFECTIVE PAGES

*Zero in this column indicates an original page.

5-9 5-10 – 5-25 5-26 – 5-27 5-28 –5-29 5-30 5-31 – 5-32 5-33 5-34 – 5-36 5-37 – 5-38 5-39 – 5-44 5-45 – 5-46 5-47 – 5-55 5-56 – 5-57 5-58 – 5-60 5-61 5-62 – 5-64 5-65 – 5-69 5-70 5-71 – 5-103 5-104 5-105 – 5-114 5-115 5-116 – 5-119 5-120 – 5-122 5-123 – 5-125 5-126 5-127 – 5-152 5-153 – 5-155 5-156 – 5-163 5-164 – 5-166 5-167 – 5-174 5-175 – 5-176 5-177 – 5-186 5-187 5-188 – 5-191 5-192 5-193 5-194 5-195 – 5-196 6-1 6-2 Blank 6A-1 – 6A-22 6B-1 – 6B-16 7-1 7-2 Blank 7A-1 – 7A-49 7A-50 Blank 7B-1 – 7B-2 7B-3 – 7B-15 7B-16 7B-17 Added 7B-18 Blank Added 7C-1 7C-2 7C-3 – 7C-15 7C-16 7C-17 Added 7C-18 Blank Added

8-1 – 8-25 8-26 Blank 9-1 9-2 – 9-3 9-4 9-5 9-6 9-7 9-7.1 – 9-7.3 9-7.4 Added 9-8 9-9 – 9-10 9-11 – 9-12 9-13 – 9-14 9-15 – 9-23 9-24 Blank 10-1 10-2 10-3 10-4 10-4.1 10-4.2 10-4.3 – 10-4.4 10-5 10-6 – 10-7 10-8 10-9 10-10 – 10-12

Change 10 B

C Change 10

Status Page This page is published with each change package for Flight Manual Program publications. It contains a listing of the affected Flight Manual and its related Supplements and Checklists current on the date of this publication. However, formal Safety and Operational Supplements that are issued after the publication of this change, will contain a more current version of the status page. Changes or revisions that are in production are shown in parentheses.

AIRCREW FLIGHT MANUAL BASIC DATE CHANGE NO./DATE

TO 1C-130H-1-1 15 March 2001 Change 10/19 February 2010

SAFETY AND OPERATIONAL SUPPLEMENTS DATE SHORT TITLE

INCORPORATED, RESCINDED OR DELETED SUPPLEMENTS

TABLE OF CONTENTS

PART PAGE

1 INTRODUCTION........................................................................................................... 1-1

1A AIRSPEED CALIBRATION CHARTS H EE HN MP .......................................... 1A-1

1B AIRSPEED CALIBRATION CHARTS HP WC ME MP ..................................... 1B-1

1C AIRSPEED CALIBRATION CHARTS EH .............................................................. 1C-1

1D AIRSPEED CALIBRATION CHARTS AC HR AU ............................................. 1D-1

1E AIRSPEED CALIBRATION CHARTS LC .............................................................. 1E-1

2 ENGINE POWER AND FUEL FLOW......................................................................... 2-1

3 TAKE-OFF PERFORMANCE....................................................................................... 3-1

4 CLIMB PERFORMANCE ............................................................................................. 4-1

5 RANGE ........................................................................................................................... 5-1

6 ENDURANCE ................................................................................................................ 6-1

6A ENDURANCE CHARTS ............................................................................................. 6A-1

6B COMBAT LOITER ENDURANCE AC AU .......................................................... 6B-1

7 SEARCH AND AIR REFUELING................................................................................ 7-1

7A SEARCH....................................................................................................................... 7A-1

7B AIR REFUELING − TANKER AIRPLANES............................................................. 7B-1

8 DESCENT PERFORMANCE........................................................................................ 8-1

9 LANDING PERFORMANCE........................................................................................ 9-1

10 MISSION PLANNING ................................................................................................ 10-1

Change 5 i/(ii blank)

7C AIR REFUELING – TANKER AIRPLANES WITH ROSEMOUNT

PITOT-STATIC SYSTEM ...............................................................................7C-1

CGTO 1C--130H--1--1 TP--8

1--1

This TOPS page adds the following guidance.

GUIDANCE FOR USE OF AFTO 1C--130H--1--1

1. Throughout the performance manual, the phrase MAJOR COMMAND (MAJCOM) approval is synonymous with COMMANDING OFFICER approval.

2. Coast Guard performance data should be computed utilizing 100 percent engine data.

Engines operating at less than 95 percent require COMMANDING OFFICER approval.

3. COMMANDING OFFICER approval for Tactical Takeoffs (non--assault qualified crew criteria) is only required when refusal speed is less than rotation speed.

4. Coast Guard tactical takeoff operations and performance data will normally be computed with non--assault qualified crew criteria. Use of assault qualified crew criteria requires COMMAND- ING OFFICER approval.

5. Coast Guard crews are not authorized to conduct reduced power takeoffs.

6. All take--off data will be computed using the “without nosewheel steering” corrections as appli-cable. If required for mission accomplishment, nosewheel steering corrections may be used for dry, paved surfaces (RCR=23) at the pilot’s discretion.

PART 1. INTRODUCTION

TABLE OF CONTENTS

Contents Page

PURPOSE OF PERFORMANCE CHARTS ..................................................................................... 1-1

PERFORMANCE CHART SERIALIZATION .................................................................................. 1-2

AIRPLANE CONFIGURATIONS...................................................................................................... 1-2

CHART EXPLANATION ................................................................................................................... 1-7

TERMS, ABBREVIATIONS, AND SYMBOLS ................................................................................ 1-7

COMPRESSIBILITY AND TEMPERATURE CORRECTIONS ................................................... 1-10

AIRSPEED INDICATION CORRECTION (CALIBRATION)....................................................... 1-12

LIST OF CHARTS

Figure Number Title Page

1-1 Compressibility Correction To Calibrated Airspeed .......................................... 1-13

1-2 Temperature Correction....................................................................................... 1-14

1-3 Density Altitude Chart ........................................................................................ 1-16

1-4 Density Altitude Table ......................................................................................... 1-19

1-5 ICAO Standard Atmosphere Table ..................................................................... 1-21

1-6 Temperature Conversion...................................................................................... 1-23

1-7 Altitude Pressure Correction Table .................................................................... 1-25

T56-A-15 engines and Hamilton SundstrandPURPOSE OF PERFORMANCE CHARTS.

54H60-91 propellers. Engine data for 100, 98, The performance charts are provided to plan and 95 percent specification engines are pro-complete missions from take-off to landing for vided. The engine performance is based on the normally encountered operating conditions. ICAO standard atmosphere, using JP-8 fuel at The performance is based on operating proce- 6.8 pounds per gallon with a Lower Heating dures and conditions that are explained in the Value of 18,400 BTU per pound, and 100 per-text or shown on the charts. These procedures cent engine RPM (13,820 RPM). The baseline and conditions must be followed in order to power extraction from the engines is that realize the charted performance for the air- required to drive 40/60 KVA generators. No plane. The operating procedures are consistent factors of conservatism are used in establishing with the normal procedures in Section II, the the airplane performance. If unusual condi-emergency procedures in Section III, and the tions are encountered, for which operating pro-all weather procedures in Section IX of the cedures are not established, the operating per-applicable Flight Manual. sonnel are expected to use their best judgment under the existing circumstances.The data for each specific airplane series are based on the results of Category II flight tests of the airplane with Rolls-Royce Allison

1-1

See Coast Guard TOPS 8 on previous page array, external fuel tanks, multiple disc 2,030PERFORMANCE CHART SERIALIZATION.

PSI brakes, gray (non-gloss) paint and walk-way paint. Changes in configuration or seriesThis manual contains performance charts for generally result in different performancevarious series of C-130 airplanes equipped with levels. These performance levels are related toT56-A-15 engines. Where necessary, series the magnitude of drag added to or subtractedcodes located under the title block of the charts identify the airplane series for which the chart from the baseline drag.

is to be used. The series codes and applicability are as follows:

AC AC-130H Airplanes Charts are included which permit the determi-nation of performance data for a specific air-AU AC-130U Airplanes plane series or configuration if the drag index change is known. For simplicity, drag changeEE EC-130E Airplanes is identified as a drag index with the baseline configuration drag index being equal to zero.EH EC-130H Airplanes The drag indexes for the various series/configurations are tabulated below andH C-130H Airplanes must be used with the appropriate charts in

HP this manual.HC-130P Airplanes

HN HC-130N Airplanes

HR C-130 Series Airplanes (with Rosemount pitot-static system)

LC LC-130H Airplanes

ME MC-130E Airplanes

MP MC-130P Airplanes

WC WC-130H Airplanes

Charts without codes apply to all airplanes cov-ered by this manual.

Parts of this manual are divided into subparts for specific airplanes. This allows the manual to be tailored to a specific airplane by removing parts that are not applicable.

AIRPLANE CONFIGURATIONS.

The baseline performance data in this manual are for USAF series C-130H airplanes (AF74-01658 and up) with 40/60 KVA genera-tors, long wire HF antennas, the AN/APN-169C(V) Enhanced Station Keeping Equipment (SKE) top and bottom radome

1-2 Change 4

H

Change 7 1-3

Various Series/Configuration Drag Indexes

Airplane Configuration Drag Index

C-130H (Baseline)

With External Fuel Tanks, Long Wire HF Antennas, SATCOM, AN/APN-169C(V) Enhanced SKE Top and Bottom Radomes, Gray (Non-Gloss) Paint, and Walkway Paint.

AC-130H With External Fuel Tanks/Pylons, Long Wire HF Antennas, Crew Entrance Door Removed, 4 Engine IR Shields, 40 mm and 105 mm Guns, IDS Ball, DIRCM Transmit-ters, Gray (Non-Gloss) Paint, and Walkway Paint, SATCOM and MATT Antenna, Aft Oberver - Area, UARRSI, Blisters, Air Deflectors, AN/APQ-150, ECM Antennas (AN/

ALR-69, AN/ALE-40/47, AN/AAR-44, AN/APR-46, AN/ALQ-172).

Series Equipment:

40 mm Gun 105 mm Gun Crew Entrance Door Removed Engine IR Shields (4) External Fuel Tanks/Pylons (2) External Tanks only (2) External Tank Pylons only (2) IDS Ball AN/AAQ-24(V)6 Transmitters and MWS Sensors (DIRCM) AN/AAQ-24(V)6 Blanking Plates (DIRCM) SATCOM and MATT Antenna Aft Observer - Area Refueling System (UARRSI)

AN/ALQ-172

AN/AAR-44

AN/APR-46 (2)

AN/ALE-40/47

AN/ALR-69

AN/APQ-150

AN/APN-169 SKE System Removal from C-130H Baseline

NOTE

The 105 mm gun without the AN/APQ-150 dome is 33.

108.4

0.4 -9

AC-130U With External Fuel Tanks/Pylons, 4 Engine IR Shields, All Guns (105 mm Gun extended), ALLTV Turret, IDS Turret/Ball, **DIRCM Transmitters, Gray (Non-Gloss) Paint, Walkway Paint, SATCOM and MATT Antennas, HF Probe Antenna, Aft Observer Area, UARRSI, Blisters, Air Deflectors, ECM Antennas (AN/ALR-69, AN/ALE-40/47, AN/AAR-44, AN/ALQ-172, AN/APR-46), Miscellaneous AC-130U Structure Mods, Mis-cellaneous Nav and Communications Equipment, E-TCAS.

Series Equipment:

Engine IR Shields (4) External Fuel Tanks/Pylons (2) External Fuel Tank Pylons Only (2) 25 mm Guns 40 mm Gun 105 mm Gun (Retracted) 105 mm Gun (Extended) **AN/AAQ-24(V)6 Transmitters and MWS Sensors (DIRCM) **AN/AAQ-24(V)6 Blanking Plates (DIRCM) ALLTV Turret IDS Turret/Ball ****IDS Fairing SATCOM and MATT Antenna HF Probe Antenna Aft Observer Area Refueling System (UARSSI)

-6.5

0.4

1-4 Change 7

AC-130U

CONTINUED

AN/AAR-44

AN/ALE-40/47

AN/ALR-69

AN/APR-46 (2)

AN/ALQ-172

Miscellaneous AC-130U Structural Modifications Miscellaneous Nav and Communications Equipment AN/APN-169 SKE System Removal from C-130H Baseline HF Long Wire Antenna Removal from C-130H Baseline ** Airplanes modified by TO 1C-130(A)U-588 ****Airplanes modified by TO 1C-130(A)U-639

0.8 -9 -3

EC-130H

(Compass Call)

With Spear Pods, Long Wire HF Antennas, SATCOM, Gray (Non-Gloss) Paint, and Walkway Paint, UARSSI, 8 UHF and 4 VHF-AM Blade Antennas, SSAC Condenser Pods, Mid-Band Antenna Radomes, AITG Antennas, DF SILO Antennas, DF Retract-able Antennas, Low Band Transmit Antennas, E-TCAS Antenna, SPS (AN/AAR-54 and AN/ALE-47) and NCCT Antenna. External Fuel Tanks are not calculated into the base-line drag index.

Series Equipment:

LBT Antenna Quadrants LBT Antenna Strakes External Fuel Tank SPEAR Pods/Pylons SPEAR Pylons Only SPS (AN/AAR-54 and AN/ALE-47)

AITG

E-TCAS

NCCT

83.2

4.5 0.5

HC-130N

and

HC-130P

Baseline C-130H plus Refueling Pods and Pylons, AN/APN-169C(V) Enhanced SKE Top and Bottom Radomes Removed, ALR-69, and ALE-40/47 Antennas, AN/AAR-47, IDS Ball/Turret, and E-TCAS.

HC-130(H)N With External Fuel Tanks, Refueling Pods and Pylons, Flush HF Antennas, AN/APN- 169C(V) Enhanced SKE Top and Bottom Radomes Removed, Defensive Systems, AN/ APX-76D IFF Interrogator Antenna, Gray (Non-Gloss) Paint, and Walkway Paint.

LC-130H

L1

With External Fuel Tanks, Long Wire HF Antennas, Polyurethane Gloss Paint, and Walkway Paint and SATCOM.

With Skis Retracted With Skis Extended

LC-130H

L2

With External Fuel Tanks, Flush HF Antennas, Polyurethane Gloss Paint, and Walkway Paint and SATCOM.

With Skies Retracted With Skis Extended

Airplane Configuration Drag Index

Change 7 1-5

The following table provides drag index values for individual items or equipment, and changes in configuration.

MC-130E With External Fuel Tanks, Refueling Pods and Pylons, Long Wire HF Antennas, Defen-sive Systems, Gray (Non-Gloss) Paint, and Walkway Paint.

IRCM Pods (2) ***AN/AAQ-24(V)6 (DIRCM) Transmitters and MWS Sensors DIRCM Transmitters/Fairings (2) DIRCM MWS Sensors ***DIRCM Transmitter Blanking Plates Installed (2) ******AN/ALR-69A(V) RWR Antennas and Fairings ***Airplanes modified by TO 1C-130(M)E-525 ******Airplanes modified by TO 1C-130(M)E-543

MC-130P Baseline C-130H plus Refueling Pods and Pylons, AN/APN-169(V) Enhanced SKE Top and Bottom Radomes Removed, Fulton Radome, IDS Ball/Turret, ALR-69, ALE-40/47, AN/AAR-44 and E-TCAS.

MC-130W Baseline C-130H, Refueling Pods and Pylons (IARS), SATCOMS (2), LAIRCM (Trans-mitters/Fairings), IDS Ball/Turret, ALE 40/47 dispensers, AAR-44 IR Sensor, AN/ALR- 69 RWR, APX-116, UARRSI, Loadmaster Signal Lights, JC2C Permanent Antennas, ETCAS.

JC2C Mission Antennas (when installed) JC2C Permanent Antennas In-Flight Refueling Pods and Pylons (IARS)

SATCOM

LAIRCM

IDS Ball/Turret

ALE-40/47

AAR-44

AN/ALR-69

APX-116

Refueling System (UARSSI) Loadmaster Signal Lights Long Wire Antennas

65.4

.4 -3

WC-130H With External Fuel Tanks, Long Wire HF Antennas, U-1 Foil System, AN/APN-169C(V) Enhanced SKE Top and Bottom Radomes Removed, Polyurethane Gloss Paint, and Walkway Paint.

-7

Item Drag Index

AN/ALQ-57 Infrared Countermeasure System 6

AN/AAQ-24(V)13 Large Aircraft Infrared Countermeasures (LAIRCM) System 10

MAFFS II S- duct 4

AN/APX-76D IFF Interrogator Antenna 4

SATCOM 2

AN/APN-169C(V) Enhanced SKE:

Top Radome Bottom Radome

ATO (8 Bottles) 70

Airplane Configuration Drag Index

1-6 Change 6

The following table provides drag index values of defensive systems along with some individual components of defensive systems.

External Fuel Tanks and Pylons 18

Refueling Pods and Pylons (Sargent Fletcher) 18

Fulton Radome 1

Gray (Non-Gloss) Paint 3

Long Wire HF Antennas 3

Polyurethane Gloss Paint -3

No Paint -3

U-1 Foil System (WC-130H) 5

Walkway Paint 6

IDS Turret (AN/AAQ-17/22A/36) 3

IDS Ball (AN/AAQ-17/22A/36) 7

IRCM Pods (2) 6

E-TCAS 2

****DIRCM Transmitters/Fairings (2) ****DIRCM MWS Sensors (5) ****DIRCM Transmitters Blanking Plates and Fairings ****Airplanes modified by TO 1C-130(A)H-619, TO 1C-130(A)U-588 and TO 1C-130(M)E-525

Cook Radome:

Take-off/Climb Cruise Refueling/Endurance

Yokes:

Retracted Extended

Item Drag Index

Defensive Systems For Airplanes (AF91-1231 and UP) 8

Missle Warning/Defensive System (TO 1C-130-1344 - Snow Storm) 7

AN/QRC 84-02A (2) Mounted On Sargent Fletcher Pylon/MAU-12 Rack Combinations 20

AN/QRC 84-02A Pods (2) Mounted Directly To External Fuel Tanks 12

*****AN/AAQ-24(V)6

*****Airplanes modified by TO 1C-130(A)H-619, TO 1C-130(A)U-588 and TO 1C-130(M)E-525

AN/AAR-44 3

Item Drag Index

RBRackley TOPS 9 Next

CGTO 1C-130H-1-1TP-9

1-6

This TOPS page removes Coast Guard 1500 Series with SLAR and adds information for the 1721.

PERFORMANCE CHART

SERIALIZATION

H C-130H Airplanes – correct series code for Coast Guard C-130s with -15 engines.

HR

C-130 Series Airplanes with Rosemount Pitot-Static System-correct series code for

CG 1717-1721.

CONFIGURATION PERFORMANCE MANUAL DRAG INDEX W/ CASPER BALL

1500 Series CGTO 1C-130H-1-1 -15 -9.1

1700-1720 and 1790 CGTO 1C-130H-1-1 -12.5 -5.6

1721 CGTO 1C-130H-1-1 -7 -0.1

Change 9 1-7

NOTE

The effects of increased environmental control capability through the use of H Packs, along with the use of higher capacity 60/90 KVA generators, result in differences in engine performance relative to the base-line C-130H airplane. These differences have been transformed into equivalent drag index levels in order to schedule perfor-mance in this manual. The equivalent drag index levels are defined below for the vari-ous flight segments under the definition of drag for equipment on specific series of airplanes. There are two exceptions to this:

one exception is the take-off segment (where the effects are represented by an increase in take-off factor). The other is the landing segment where operation of the H Pack is irrelevant with respect to landing performance and where the effect of the equivalent drag associated with the use of the 60/90 KVA generators is inconsequen-tial. Examples of the use of these equivalent drag indexes are provided throughout the manual where applicable.

A list of equivalent drag index levels, according to flight segment, is given in the following table to represent the change in performance due to the use of H+ Packs.

AN/AAR-47 1

AN/ALE-40/47:

Forward Dispensers Aft Dispensers

AN/ALR-69:

Belly Mount Spirals Nose, Tail Spirals Compass Sail Verical Stabilizer Spirals (Airplanes modified by TO 1C-130(M)E-543)

AN/ALR-69A(V):

Nose, Tail Spirals (Airplanes modified by TO 1C-130-1840 and TO 1C-130-2016) 1

ALQ-131 Pods/Mounting Methods:

Two Sargent Fletcher pylons with two MAU-12 bomb racks installed Two Sargent Fletcher pylons with two MAU-12 bomb racks installed and two ALQ-131 pods Two WR-ALC modified A-model pylons with two MAU-12 bomb racks installed Two WR-ALC modified A-model pylons with two MAU-12 bomb racks installed and two ALQ-131 pods Two ALQ-131 Pods (Isolated)

AN/AAQ-24(V)13 LAIRCM:

SLTAs (2) Missile Warning System (MWS) Sensors (5)

Item Drag Index

Segment Equivalent Drag

Take-off Not Applicable – see PART 3 (Take-off)

Climb DIEQ = 64 – see PART 4 (Climb) and the climb ceiling schedules of PART 5 (Cruise)

Cruise DIEQ = 35 for general cruise and range determination – see PART 5 (Cruise)

Endurance DIEQ = 60 – see PART 6 (Endurance)

Search/Refu-eling

DIEQ = 60 – see PART 7 (Search)

Descent DIEQ = 60 – see PART 8 (Descent)

Landing Not Applicable

1-8 Change 6

During the climb, cruise, search/refueling/hold, and descent segments the performance degradation due to the change in generators is represented by an equivalent drag index of DIEQ 20.

NOTE

The use of 60/90 KVA generators, in lieu of 40/60 KVA generators, results in a degrada-tion in engine performance.

NOTE

During take-off, the performance degrada-tion due to the change in generators is rep-resented by an increase in take-off factor of fTO 0.1.

NOTE

Landing performance is not affected by the change in generators.

NOTE

See the various parts of this manual for examples of the treatment of 60/90 KVA generators.

The following table provides drag index values for gen-eral airplane variant configurations.

The tabulated drag index values shall be added to or subtracted from the Baseline Airplane Configuration, as necessary, to determine the drag index for a particular configuration.

Example 1.

GIVEN:

Airplane: C-130H.

Upper SKE Radome: Removed.

Walkway Paint: Removed.

FIND:

Drag Index.

PROCEDURE:

Baseline drag index for the C-130H is 0.

From the tabulated data, find the following:

Upper SKE Radome removed: -7

Walkway paint removed: -6

Drag Index: 0 - 7 - 6 = -13.

Example 2.

GIVEN:

Airplane: HC-130N (standard configuration).

Cargo door and ramp open.

FIND:

Total drag index in cruise.

PROCEDURE:

HC-130N drag variant from baseline: 16

From the tabulated data, find the following:

Ramp and door open: 160

Total drag index: 16 160 176.

CHART EXPLANATION.

Descriptive explanations and example problems are included in the text of each PART of the manual to illustrate the use of the performance charts. On each chart miniature illustrations are provided to show the path to follow when using the charts.

Variant Configuration Drag Index

Aft Fuselage Strakes Installed:

Climb Cruise Endurance

-4 -10

Cargo Door Open, Ramp Closed 50

Cargo Door and Ramp Open 160

Crew Entrance Door Removed 10

Gear Down (Doors Installed) 158

Main Landing Gear Doors Removed (Gear Up) (One Side Left or Right)

Nose Landing Gear Doors Removed (Gear Up)

Paratroop Doors Open, Air Deflectors Extended

Change 5 1-9

TERMS, ABBREVIATIONS, AND SYMBOLS

All bleed on All pneumatic systems operating - Air Conditioning On

Cabin Pressurization On Pneumatic Anti-icing On Engine Bleed Air Switches On

ATIS Automated Terminal Information System

ATO Assisted take-off a Speed of sound at a given altitude/temperature combination (units of knots or ft/sec) a0 Speed of sound for a sea level/standard day condition.

BTU British thermal units

CAS or VC Calibrated airspeed; indicated airspeed corrected for installation (position error)

CFL Critical field length

Balanced The distance required to continue the take-off is equal to the distance required to stop

Unbalanced Stop distance is greater than the distance to continue the take-off

Crosswind Crosswind is that component of the existing wind condition which acts perpendicular to the direction of travel.

DEG C or °C Temperature in degrees Celsius

DEG F or °F Temperature in degrees Fahrenheit

DER Departure End of Runway

DIEQ Equivalent drag index

EAS or VE Equivalent airspeed; calibrated airspeed corrected for compressibility fC Climb-out factor − the equivalent gross weight (divided by 1,000) for a Sea Level/Standard Day condition that will have the same climbout capability or profile as for a given weight/altitude/temperature combination.

EFI Electronic flight indicator

FLIP Flight information publication

FPM Feet per minute ft/nm feet/nautical mile fTO Take-off factor g Unit of acceleration (1g = 32.174 feet per second/second)

GCAS Ground collision avoidance system

GI Ground idle

GPWS Ground proximity warning system

1-10 Change 5

TERMS, ABBREVIATIONS, AND SYMBOLS

GS Ground speed; true airspeed adjusted for either head- or tailwind components

GW Gross weight

Hd Density altitude

Headwind Headwind is that component of the existing wind condition which acts opposite to the direction of travel

HP Pressure altitude

IAS or VI Indicated airspeed, the airspeed indicator reading corrected for instrument error

ICAO International Civil Aviation Organization

IFF Identification friend or foe

IFR Instrument flight rules

IGE In ground effect

In.Hg Inches of mercury: a unit for the measure of pressure

In.lb. Inch-pounds: a unit for the measure of engine torque

IOAT Indicated outside air temperature

ISA International Standard Atmosphere

K Knots, nautical miles per hour - used in conjunction with CAS, EAS, IAS, or TAS

KVA Kilo volt ampere

MATT Multi-Mission Advanced Tactical Terminal

Millibar Unit of pressure measurement in the metric system - 1 millibar = 1 dyne per square centimeter

Nau mi or Nautical mile(s) N Mi

Normal Bleed The condition corresponding to - Air Conditioning On Cabin Pressurization On Pneumatic Anti-icing Off Engine Bleed Air Regulator Valve On Engine Bleed Air Switches On

NOTE

Airplanes configured without bleed air regulators operate, in effect, in override at all times.

Bleed air extraction from the compressor is completely dependent on downstream bleed air consumption. Consequently, normal bleed for airplanes without bleed air regulators assumes all systems using bleed air are operating within normal limits and pneumatic anti-icing systems are off.

NTS Negative torque system

Change 5 1-10.1

TERMS, ABBREVIATIONS, AND SYMBOLS

OAT Outside air temperature (actual)

OBS Obstacle

OGE Out of ground effect

PA Pressure altitude

PSI Pressure in pounds per square inch

PSIG Gage pressure, pounds per square inch p Pressure at a given altitude (units of In.Hg or PSI) pO Pressure at sea level

R/C Rate of climb

R/D Rate of descent

RCR Runway condition reading

RP Reduced power

RPM Engine speed (revolution per minute)

RSC Runway surface covering

SAT Static air temp

SCNS Self-contained navigation system

SHP Engine shaft horsepower

SKE Station keeping equipment

Slug Unit of mass − 1 slug = 1 pound (mass) = 32.174 pound (weight)

SMOE Correction for air density applied to EAS (SMOE factor = )

T Temperature at a given altitude/elevation (units of °C or °F)

T0 Temperature at sea level for a standard day (units of °C or °F)

TS Temperature at a given altitude/elevation for a standard day (units of °C or °F)

T/TS Temperature ratio, T/TS = T(°F) + 459.7 or T/TS = T(°C) + 273.2

TS(°F) + 459.7 TS(°C) + 273.2

Tailwind Tailwind is that component of the existing wind condition which acts in direction of travel

TAS or VT True airspeed of the airplane − EAS or VE ×

TIT Turbine inlet temperature

TOF Take-off factor

Torque Inch-pounds torque = SHP × 4.56

VB(MAX) Maximum brake energy speed (KCAS)

VCEF Critical engine failure speed

1/ o

1/ o

1-10.2 Change 5

TERMS, ABBREVIATIONS, AND SYMBOLS

VD Maximum permissible speed

VH Structurally limited maximum level flight speed (recommended speed)

VMCA Air minimum control speed

VMCG Ground minimum control speed

VMETO Maximum effort take-off speed

VR Refusal speed

VROT Rotation speed

VS Power-off stall speed

VTO Take-off Speed

VT/WF Specific air range: air nautical miles per pound of fuel (N Mi/lb of fuel)

WF Total fuel flow in pounds per hour (lb/hr) w Specific weight of air (units of pounds per cubic foot)

ZFW Zero Fuel Weight (airplane weight excluding fuel)

∆ Indicates an increment (delta)

∆VC Compressibility correction/increment

∆VP Position error correction/increment δ Atmospheric pressure ratio (δ = p/p0) θ Atmospheric temperature ratio, θ = T(°F) + 459.7 or θ = T(°C) + 273.2 T0(°F) + 459.7 T0(°C) + 273.2 ρ Atmospheric density at altitude for a given temperature of the day (units of slugs per cubic foot)

Change 2 1-11

TERMS, ABBREVIATIONS, AND SYMBOLS

ρ 0 Atmospheric density at sea level for a standard day (ρ0 = 0.002378 slugs per cubic foot) σ Atmospheric density ratio (σ=ρ/ρ0)

SMOE factor: correction for air density applied to EAS to obtain TAS

% Percent µ Friction coefficient

1/ o

COMPRESSIBILITY AND TEMPERATURE

CORRECTIONS.

The correction to airspeed due to the compressibilityof the atmosphere is shown in figure 1-1. This chart provides the speed increments, VC for changing

CAS to EAS. Calibrated airspeed and equivalent airspeed are related by the expression:

EAS = CAS - VC or VE = VC - VC

Example.

GIVEN:

Airspeed: 200 KCAS.

Pressure altitude: 20,000 feet.

FIND:

Compressibility increment to airspeed.

PROCEDURE:

Enter the bottom of figure 1-1 with 200 KCAS and move up vertically to the given pressure altitude of 20,000 feet. Move horizontally to the left to read

VC = 2.5 knots.

TEMPERATURE DEVIATION.

The temperature correction charts of figure 1-2 permit the correction of indicated temperature read-ings for the effects of compressibility and the con-version of the resulting true temperature of the day to a version of temperature deviation relative to a standard day ISA condition.

NOTE

Indicated airspeed must be converted to calibrated airspeed.

Example.

GIVEN:

Airspeed: 200 KCAS.

Pressure altitude: 20,000 feet.

Indicated outside air temperature (IOAT):-20°C.

FIND:

True outside air temperature and its differencefrom that of a standard day.

PROCEDURE:

Enter figure 1-2, sheet 1 with 200 KCAS and move horizontally to the right to 20,000 feet.

From this point, move vertically up to an IOAT - 20°C. Move horizontally to the right and read a true outside air temperature of -28.5°C. Enter sheet 2 at the left side with the true OAT of -28.5°C and move to the right, intersecting the given pressure altitude of 20,000 feet. Move down and find a deviation from standard temperature of -4°C. This temperature condition can be referred to as that for an ISA - 4°C day.

DENSITY CORRECTION CHARTS.

The Density Altitude Chart, figure 1-3, or the Den-sity Altitude Table, figure 1-4, supply the SMOE values required to convert EAS to TAS or vice versa. In addition, the density altitude can be found, although density altitude is normally not required for performance calculations. The relationships of the various speeds are expressed by the following:

TAS = EAS x SMOE or VT = VE x 1/ o

Example.

GIVEN:

Pressure altitude: 20,000 feet.

OAT: -28.5°C from the example above.

Equivalent airspeed: 200 KEAS.

FIND: Example.

GIVEN:True airspeed.

Actual field elevation is 700 feet.PROCEDURE:

Altimeter setting is 30.02 In.Hg.Enter either sheet 2 or sheet 3 of figure 1-3 at a true OAT of −28.5oC on the bottom and move

FIND:up to intersect the 20,000−foot pressure alti-tude line. Proceed horizontally to the right

Pressure altitude for the airfield.side of the chosen chart to read SMOE = 1.36.

This occurs at a density altitude of between PROCEDURE:

19,500 and 19,600 feet (approximately 19,550 feet), which then could be used to enter sheet 2 Enter figure 1-7 with 30.02 In.Hg (30.0 In.Hg of figure 1-4 to obtain a similar value of SMOE from the left side and 0.02 In.Hg from across of about 1.36. the top of the table) and find the correction (∆

Alt) of −91 feet. Add the actual field elevation Thus, of 700 feet and the correction of −91 feet to obtain a field pressure altitude of:

VT = VE × = 200(1.36) = 272 KTAS

700 + (−91) = 609 feet.

STANDARD ATMOSPHERE TABLE.

AIRSPEED INDICATION CORRECTION

The Standard Atmosphere table, also referred (CALIBRATION).to as the International Standard Atmosphere (ISA) table, is provided as sheet 1 of figure 1-5 The airspeed indicator reading is affected by to show standard values of the atmosphere as the airflow around the airplane fuselage.

defined by the ICAO. Sheet 2 of figure 1-5 Changes in airplane attitude, configuration provides the means to convert atmospheric (wing flap and landing gear position), and prox-pressure levels between units of In.Hg and mil- imity to the ground (ground effect) vary this libars. The ICAO assumes a temperature of airflow. This affects the pressure sensed at the +15oC (59oF) and a pressure of 29.92 In.Hg as static ports of the pitot-static system, thus standard sea level conditions. The tempera- causing the airspeed indicator to read incor-ture variation (lapse rate) with altitude is rectly. This error, which varies for different approximately constant at −2oC per 1,000 feet series airplanes, is called airspeed position from sea level to 36,089 feet. At 36,089 feet, error, ∆VP. In general, calibrated airspeed and the stratosphere is assumed to begin and the indicated airspeed are related by the temperature remains constant, for all practical expression, purposes, with increases in altitude.

CAS = IAS + ∆VP or VC = VI + ∆VPThe Standard Atmosphere table shows values for each 1,000-foot increment in altitude and Conversely includes temperatures in both degrees Fahren-heit and degrees Celsius. In addition, a Tem- IAS = CAS − ∆VP or VI = VC − ∆VP perature Conversion chart, figure 1-6, is pro- The airspeed calibration charts provided invided for conversion of temperatures from one PARTs 1A through 1E include the positiontemperature scale to the other.

error correction and show the relationship of calibrated airspeed to indicated airspeed. The airspeed calibration curves are based on flightALTITUDE PRESSURE CORRECTION test data except where extended by dottedTABLE.

lines. The extended lines are extrapolated

The Altitude Pressure Correction table of fig- data. The charts are used to convert KCAS to ure 1-7 provides the correction necessary to KIAS or vice versa as requirements dictate.

determine pressure altitude when field eleva- Examples of use of the charts are provided in tion and altimeter setting (In.Hg) are known. PARTs 1A through 1E.

1-12

-2

100 125 150 175 200 225 250 275 300 325 350

CALIBRATED AIRSPEED - KNOTS

COMPRESSIBILITY CORRECTION

TO CALIBRATED AIRSPEED

C130H1(-15S)-P1-00-001

C O

M P

R E

S S

IB

IL

IT

Y

C O

R R

E C

T

IO

N

V

K N

O T

S C

SL

PRESS. ALT

- 1,000 FEET

-1

NOTE

SUBTRACT CORRECTION FROM CALIBRATED

AIRSPEED TO OBTAIN EQUIVALENT AIRSPEED.

V = V - ∆V C CE

Figure 1-1.

1-13

C130H1(-15S)-P1-01-002-1

C A

L

IB

R A

T E

D A

IR

S

P E

E D

K

N O

T S

-80

-60

-20

-40

T R

U E

O U

T S

ID

E

A

IR

T E

M P

E R

A T

U R

E

C

SL

PRESS A

LT -

1,000 FEET

-1

INDICATED OAT - °C

-30

-40

-20

-60

-70

-50

-10

TEMPERATURE CORRECTION

RECOVERY FACTOR = 0.9

COMPRESSIBILITY EFFECTS

Figure 1-2. (Sheet 1 of 2) 1-14 Change 1

C130H1(-15S)-P1-01-002-2

TEMPERATURE CORRECTION

-40 -30 -20 -10 0 10 20 30 40

TEMPERATURE DEVIATION FROM STANDARD DAY - °C

-50-60-70 50 60 70

-100

-80

-60

-40

-20

T R

U E

O U

T S

ID

E

A

IR

T E

M P

E R

AT

U

R E

°C

-120

-140

PRESS ALT

- 1,000 FEET

36,089

AND

ABOVE

SL

-1

RECOVERY FACTOR = 0.9

TEMPERATURE DEVIATION

Figure 1-2. (Sheet 2 of 2)

1-15

C130H1(-15S)-P1-00-003-1

DENSITY ALTITUDE CHART

.86

.88

.90

.92

.94

.96

.98

1.00

1.02

1.04

1.06

1.08

1.10

1.12

√σ

-12

-10

-8

-6

-4

-2

D E

N S

IT

Y

A

LT

IT

U

D E

,0

F E

E T

-70 -50 -30 -10 10 30-60 -40 -20 0 20 40 6050 70

TRUE OUTSIDE AIR TEMPERATURE - °C

14 12 10

-4

-2 S

T D

D

AY

-6

-8

-10

-12

PRESS A

LT

1,0

F

EET

Figure 1-3. (Sheet 1 of 3)

1-16

C130H1(-15S)-P1-00-003-2

DENSITY ALTITUDE CHART

1.00

1.02

1.04

1.06

1.08

1.10

1.12

1.14

1.16

1.18

1.20

1.22

1.24

1.26

1.28

1.30

1.32

1.34

1.36

D E

N S

IT

Y

A

LT

IT

U

D E

,0

F E

E T

-70 -50 -30 -10 10 30-60 -40 -20 0 20 40 6050 70

TRUE OUTSIDE AIR TEMPERATURE - °C

PRESS A

LT

1,0

F

EET

-4

-2

24 S T

D D

AY

Figure 1-3. (Sheet 2 of 3)

1-17

C130H1(-15S)-P1-00-003-3

DENSITY ALTITUDE CHART

-70 -50 -30 -10 10 30-60 -40 -20 0 20 40 6050 70

TRUE OUTSIDE AIR TEMPERATURE - °C

D E

N S

IT

Y

A

LT

IT

U

D E

,0

F E

E T

1.30

1.32

1.34

1.64

1.38

1.40

1.60

1.44

1.68

1.72

1.76

1.80

1.84

1.88

1.92

1.96

2.00

1.36

1.48

1.52

1.56

PRESS ALT

- 1

,000 FEET

S T

D D

AY

Figure 1-3. (Sheet 3 of 3)

1-18

DENSITY

ALTITUDE

(FEET)

σ

DENSITY

ALTITUDE

(FEET)

σ

DENSITY

ALTITUDE

(FEET)

σ

DENSITY

ALTITUDE

(FEET)

σ

DENSITY

ALTITUDE

(FEET)

σ

DENSITY

ALTITUDE

(FEET)

σ

C130H1(-15S)-P1-00-004-1

-1000 0.9855

-900 0.9870

-800 0.9884

-700 0.9898

-600 0.9913

-500 0.9927

-400 0.9942

-300 0.9956

-200 0.9971

-100 0.9985

0 1.0000

100 1.0015

200 1.0029

300 1.0044

400 1.0059

500 1.0074

600 1.0088

700 1.0103

800 1.0118

900 1.0133

1000 1.0148

1100 1.0163

1200 1.0178

1300 1.0193

1400 1.0208

1500 1.0223

1600…