AIRCREW WEAPONS DELIVERY MANUAL (NONNUCLEAR) B-52/AGM-86C/D USAF SERIES

Transcription

1 AIRCREW WEAPONS DELIVERY MANUAL (NONNUCLEAR) B-52/AGM-86C/D USAF SERIES B-52/AGM-86C/D AIRCRAFT WEAPONS THE BOEING COMPANY F C-1116 F D-0066 This manual contains unverified procedures. Refer to the validation/verification status page(s) prior to performing any operation or maintenance procedure. THIS PUBLICATION IS INCOMPLETE WITHOUT CLASSIFIED SUPPLEMENT T.O. 1B-52H SEE T.O. 0-1-CD-1 FOR CURRENT STATUS OF FLIGHT MANUALS, SAFETY SUPPLEMENTS, OPERATIONAL SUPPLEMENTS, AND FLIGHT CREW CHECKLISTS. COMMANDERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION TO THE ATTENTION OF ALL AIR FORCE PERSONNEL CLEARED FOR OPERATION OF SUBJECT AIRCRAFT. DISTRIBUTION STATEMENT E Distribution authorized to the Department of Defense Components only, due to Direct Military Support, 29 October Other requests shall be referred to 327 BMSG/EN, Tinker AFB, OK 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 et seq. Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive HANDLING AND DESTRUCTION NOTICE Comply with distribution statement and destroy by any method that will prevent disclosure of contents or reconstruction of the document. Demil code D. PUBLISHED UNDER AUTHORITY OF THE SECRETARY OF THE AIR FORCE 1 JUNE 1999 CHANGE 11 1 JUNE 2006

2 Technical orders are normally distributed promptly after printing. Date(s) shown on the title page (lower right corner) are for identification only. These are not distribution dates. Processing time sometimes causes distribution to only appear to have been delayed. LIST OF EFFECTIVE PAGES NOTE: INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES. The portion of the text affected by the changes is indicated by a vertical line in the outer margins of the page. Dates of issue for original and changed pages are: Original 0 1 Jun 99 Change 1 1 Oct 99 Change 2 1 Aug 00 Change 3 30 June 01 Change 4 30 Nov 01 Change 5 1 Mar 02 Change 6 1 Sep 02 Change 7 1 Apr 03 Change 8 1 Dec 03 Change 9 1 Dec 04 Change 10 1 Jul 05 Change 11 1 Jun 06 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 288 CONSISTING OF THE FOLLOWING: Page Change Page Change Page Change Page Change No. No. No. No. No. No. No. No. * Title *A V/VS-1 V/VS-9 Added.. 10 V/VS-10 Blank Added Flyleaf Flyleaf-2 Blank i ii iii v vi Blank Blank * 1-6A 1-6B C 1-6D E 1-6F Deleted * Blank * A 1-40B Added * * A 1-44D Added * 1-46A B C 1-46D Added A 1-56B Deleted A 1-66B C Added * 1-66D E Added * 1-66F G 1-66H Added * A 1-68D Added A 1-70B Added A B * A 1-76H Added Added Blank Added A 2-10B A 2-14B C 2-14D Added * * Blank A Added B Blank Added Blank Blank A 7-12B Deleted Added A 7-18F Deleted G 7-18H Deleted A 7-24B Deleted * A 7-46B Deleted Added Glossary-1 Glossary Glossary-3 Added Glossary-4 Blank Added.. 10 Index-1 Index CURRENT ABBREVIATED CHECKLIST AGM-86C/D CALCM MISSILE Abbreviated Flight Crew Checklist T.O. 1B-52H CL-1 1 Jun 99 Change 9 1 Jun 06 Upon receipt of the second and subsequent changes to this technical order, personnel responsible for maintaining this publication in current status will ascertain that all previous changes have been received and incorporated. Action should be taken promptly if the publication is incomplete. *The asterisk indicates pages changed, added, or deleted by the current change. ADDITIONAL COPIES OF THIS PUBLICATION MAY BE OBTAINED BY USAF ACTIVITIES IN ACCORDANCE WITH T.O A Change 11 USAF

3 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) (B) (B) TCTO Listings (P, PG v) 5/16/03 A B-52 Carrier Aircraft (P, PG 1-3) 5/16/03 A B-52 Carrier Aircraft (S, PG 1-3) 5/16/03 A Circuit Breaker Panels (F: 1-7, 2/3, PG 1-14) 5/16/03 A OAS Avionics System (P, PG 1-17) 5/16/03 A OAS Avionics System (OAS) Interface (S, PG 1-17) 5/16/03 A Location/Station Selection (P, PG 1-18) 5/16/03 A Ejector Unlock Consent (P, PG 1-18) 5/16/03 A Weapon Power Control Command (P, PG ) 5/16/03 A Ready-To-Launch Command (P, PG 1-19) 5/16/03 A Manual Launch Command (P, PG 1-19) 5/16/03 A OAS/Missile Data Flow (F: 1-10, PG 1-22) 5/16/03 A Missile Jettison (S, PG 1-30) 5/16/03 A Missile Jettison Switch (P, PG 1-30) 5/16/03 A Pilot s Jettison Controls and Indicators (F: 1-17, PG 1-31) 5/16/03 A Stores Management Overlay (S, PG 1-37) 5/16/03 A SMO Initialization (P, PG 1-37) 5/16/03 A SMO Termination (P, PG ) 2/01/03 A SMO Reconfiguration (P, PG 1-38) 5/16/03 A Controls and Displays Commands (P, PG 1-38) 5/16/03 A OAS Power Control Panel Commands (P, PG 1-39) 5/16/03 A LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-1

4 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) Weapon Control Panel Commands (P, PG 1-39) 5/16/03 A Pilot s Munitions Consent Panel Commands (P, PG 1-40) 5/16/03 A Pilot s Bomb Bay and Missile Jettison Control Switch (P, PG 1-40) 5/16/03 A IKB Commands (P, PG A) 5/16/03 A MFD Displays (P, PG 1-40A) 5/16/03 A SMO MFD Displays (P, PG 1-40B) 5/16/03 A Prime Mission Data (P, PG 1-40B) 5/16/03 A Control Function (CF) Displays (S, PG 1-42) 5/16/03 A Weapon Supervision Menu (P, PG 1-42) 5/16/03 A Strike Mode Command (P, PG 1-42) 5/16/03 A PART SIM Mode Command (P, PG 1-42) 5/16/03 A FULL SIM Mode Command (P, PG 1-43) 5/16/03 A SMO Control Function Commands (F: 1-22, 1/2, PG 1-44) 5/16/03 A SMO Control Function Commands (F: 1-22, 2/2, PG 1-44A) 5/16/03 A Control Function Menu (F: 1-23, 1/2, PG 1-44B) 5/16/03 A Control Function Menu (F: 1-23, 2/2, PG 1-44C) 5/16/03 A Weapon Supervision Menu (F: 1-24, 1/2, PG 1-44D) 5/16/03 A Weapon Supervision Menu (F: 1-24, 2/2, PG 1-45) 5/16/03 A CALCM Supervision Menu (P, PG 1-46) 5/16/03 A Crypto Key Override Command (P, PG 1-46) 5/16/03 A CALCM Supervision Menu (F: 1-25, 1/2, PG 1-46A) 5/16/03 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-2

5 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) CALCM Supervision Menu (F: 1-25, 2/2, PG 1-46B) 5/16/03 A Weapon Erase Command CF-55F (P, PG 1-46C) 5/16/03 A CALCM Auto Targeting Mode CF-550 (P, PG 1-46C) 5/16/03 A Go/No-Go Test CF-551 (P, PG 1-46C) 5/16/03 A System Interface Test (SIT) CF-552 (P, PG 1-46C) 5/16/03 A Manual SAIR Command CF-553 (P, PG 1-46C 1-46D) 5/16/03 A Classified Data Erase Command CF-555 (P, PG 1-46D) 5/16/03 A Manual Target Command CF-556,nn (P, PG 1-46D) 5/16/03 A Flex Targeting Selection Command CF-557,nn (P, PG 1-47) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 1/9, PG 1-48) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 2/9, PG 1-49) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 3/9, PG 1-50) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 4/9, PG 1-51) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 5/9, PG 1-52) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 6/9, PG 1-53) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 7/9, PG 1-54) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 8/9, PG 1-55) 5/16/03 A CF-557,nn Flex Target Input Display (F: 1-26, 9/9, PG 1-56) 5/16/03 A Direct Targeting Input Screen CF-558,nn (P, PG 1-57) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 1/10, PG 1-58) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 2/10, PG 1-59) 5/16/03 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-3

6 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) CF-558 Direct Targeting Input Display (F: 1-27, 3/10, PG 1-60) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 4/10, PG 1-61) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 5/10, PG 1-62) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 6/10, PG 1-63) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 7/10, PG 1-64) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 8/10, PG 1-65) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 9/10, PG 1-66) 5/16/03 A CF-558 Direct Targeting Input Display (F: 1-27, 10/10, PG 1-66A) 5/16/03 A Target/Retarget-All Command CF-559 (P, PG 1-66B) 5/16/03 A SMO Menu (CF-62) (P, PG 1-66C) 5/16/03 A Shutdown (CF-67) (P, PG 1-66D) 5/16/03 A ECU PWR ORIDE (CF-68) (P, PG 1-66D) 5/16/03 A CF-6 FCP Supervision Menu (F: 1-28, 1/2, PG 1-66E) 5/16/03 A CF-6 FCP Supervision Menu (F: 1-28, 2/2, PG 1-66F) 5/16/03 A CF-62 SMO Load Menu (F: 1-29, 1/2, PG 1-66G) 5/16/03 A CF-62 SMO Load Menu (F: 1-29, 2/2, PG 1-66H) 5/16/03 A Mission Supervision Menu (CF-8) (P, PG 1-67) 5/16/03 A B-52 Mission Data Load Display (CF-81) (P, PG 1-67) 5/16/03 A Weapon Group Selection Menu (P, PG 1-68) 5/16/03 A CF-8 Mission Supervision Menu (F: 1-30, 1/2, PG 1-68A) 5/16/03 A CF-8 Mission Supervision Menu (F: 1-30, 2/2, PG 1-68B) 5/16/03 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-4

7 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) CF-81 Mission Data Load Display (F: 1-30A, 1/2, PG 1-68C) 5/16/03 A CF-81 Mission Data Load Display (F: 1-30A, 2/2, PG 1-68D) 5/16/03 A CF-82A, CF-82B, CF-82C Wpn Grp Selection Screen (F: 1-30B, PG 1-69) 5/16/03 A Send Targeting Data Command (P, PG 1-70) 5/16/03 A CF-DF AGM-86D Fuze Data Input Disp (F:1-30C, 1/5, PG 1-70A) 5/16/03 A CF-DF AGM-86D Fuze Data Input Disp (F:1-30C, 2/5, PG 1-70B) 5/16/03 A CF-DF AGM-86D Fuze Data Input Disp (F:1-30C, 3/5, PG 1-71) 5/16/03 A CF-DF AGM-86D Fuze Data Input Disp (F:1-30C, 4/5, PG 1-72) 5/16/03 A CF-DF AGM-86D Fuze Data Input Disp (F:1-30C, 5/5, PG 1-72A) 5/16/03 A Format Displays (S, PG 1-74) 5/16/03 A Status and Inventory Display (FRMT-7) (P, PG 1-74) 5/16/03 A Weapon Group Assignment Data Display (P, PG 1-75) 5/16/03 A Stores Inventory Summary Display (FRMT-77) (P, PG 1-75) 5/16/03 A Format Commands (F:1-32, PG 1-75) 5/16/03 A Format Menu (F:1-33, 1/2, PG 1-76) 5/16/03 A Format Menu (F:1-33, 2/2, PG 1-76A) 5/16/03 A FRMT-6 PME Status Display (F:1-34, 1/3, PG 1-76A) 5/16/03 A FRMT-6 PME Status Display (F:1-34, 2/3, PG 1-76B) 5/16/03 A FRMT-6 PME Status Display (F:1-34, 3/3, PG 1-76C) 5/16/03 A FRMT-7 and FRMT-7xy Status and Invent Disp (F:1-35, 1/5, PG 1-76D) 12/1/04 A FRMT-7 and FRMT-7xy Status and Invent Disp (F:1-35, 2/5, PG 1-76E) 12/1/04 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-5

8 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) FRMT-7 and FRMT-7xy Status and Invent Disp (F:1-35, 3/5, PG 1-76F) 2/01/05 A FRMT-7 and FRMT-7xy Status and Invent Disp (F:1-35, 4/5, PG 1-76G) 2/01/05 A FRMT-7 and FRMT-7xy Status and Invent Disp (F:1-35, 5/5, PG 1-76H) 2/01/05 A CF-DF or CF-DB Wpn Grp Assign Data Disp (F:1-35A, 1/3, PG 1-77) 5/16/03 A CF-DF or CF-DB Wpn Grp Assign Data Disp (F:1-35A, 2/3, PG 1-78) 5/16/03 A CF-DF or CF-DB Wpn Grp Assign Data Disp (F:1-35A, 3/3, PG 1-79) 5/16/03 A FRMT-77 Stores Inventory Summary Disp (F:1-35B, 1/2, PG 1-80) 5/16/03 A FRMT-77 Stores Inventory Summary Disp (F:1-35B, 2/2, PG 1-81) 5/16/03 A CALCM Direct Target Program Disp (P, PG 1-83) 5/16/03 A Weapon Targeting Commands (P, PG 1-84) 5/16/03 A SMO Launch Point Program Display (F:1-39, 2/3, PG 1-87) 5/16/03 A SMO Launch Point Program Display (F:1-41, 1/5, PG 1-93) 5/16/03 A SMO Launch Point Program Display (F:1-41, 2/5, PG 1-94) 5/16/03 A SMO Launch Point Program Display (F:1-41, 3/5, PG 1-95) 5/16/03 A SMO Launch Point Program Display (F:1-41, 4/5, PG 1-96) 5/16/03 A SMO Launch Point Program Display (F:1-41, 5/5, PG 1-97) 5/16/03 A General (P, PG 2-3) 5/16/03 A CALCM SMO Loading Checklist (PG 2-10) 5/16/03 A Weapon Check Checklist (PG B) 5/16/03 A Missile Power Application Checklist (PG ) 2/01/05 A Target/Retarget All Checklist (PG 2-14A 2-14B) 5/16/03 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-6

9 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) Mission Substitution Checklist (PG 2-15) 5/16/03 A Manual Retargeting Checklist (PG 2-16) 5/16/03 A Missile Jettison Procedures (RN/N Reads) (PG 3-2) 5/16/03 A Missile Jettison Procedures (RN/N Reads) (Cont) (PG 3-3) 2/01/05 A Telemetry Power Transfer Command CF-55C (P, PG 4-2) 2/01/05 A Launch (P, PG 4-3) 5/16/03 A SMO Capabilities (P, PG 7-3) 5/16/03 A Strike Capabilities (P, PG 7-3) 5/16/03 A MIU Power Application (P, PG 7-4) 5/16/03 A Mission Data (P, PG 7-9) 5/16/03 A Preplanned Mission (P, PG 7-9) 5/16/03 A Automatic Targeting Process (P, PG 7-10) 5/16/03 A Manual Targeting Process (P, PG 7-11) 5/16/03 A Weapon Targeting Commands (P, PG 7-12) 5/16/03 A Manual Target Command (P, PG 7-14) 5/16/03 A Target/Retarget All Command (P, PG 7-14) 5/16/03 A Target Location (P, PG 7-16) 5/16/03 A Impact Angle (P, PG 7-17) 5/16/03 A Flex Target Mission Data Entry (P, PG ) 2/01/05 A Direct Target Data Entry (P, PG ) 2/01/05 A In-Range Determination (P, PG 7-25) 5/16/03 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-7

10 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) Manual SAIR (P, PG 7-25 ) 5/16/03 A Direct SAIR (P, PG 7-27) 5/16/03 A Automatic Retargeting (P, PG 7-31) 5/16/03 A Launch Determination (P, PG 7-33) 5/16/03 A Auto Launch Determination (P, PG ) 5/16/03 A Man Launch Determination (P, PG 7-34) 5/16/03 A Manual Jettison (P, PG 7-36) 5/16/03 A Simulated Weapons (P, PG 7-38) 5/16/03 A Termination Of SIM Mode (P, PG 7-39) 5/16/03 A SIT/MIT and CF-552 (P, PG 7-39) 5/16/03 A Missile/Station Master Faults (F: 7-9, 1/10, PG 7-42) 2/01/05 A Missile/Station Master Faults (F: 7-9, 2/10, PG 7-43) 2/01/05 A Missile/Station Master Faults (F: 7-9, 3/10, PG 7-44) 2/01/05 A Missile/Station Master Faults (F: 7-9, 4/10, PG 7-45) 2/01/05 A Missile/Station Master Faults (F: 7-9, 5/10, PG 7-46) 2/01/05 A Missile/Station Master Faults (F: 7-9, 6/10, PG 7-47) 2/01/05 A Missile/Station Master Faults (F: 7-9, 7/10, PG 7-48) 2/01/05 A Missile/Station Master Faults (F: 7-9, 8/10, PG 7-49) 2/01/05 A Missile/Station Master Faults (F: 7-9, 9/10, PG 7-50) 2/01/05 A Missile/Station Master Faults (F: 7-9, 10/10, PG 7-51) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 1/8, PG 7-52) 2/01/05 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-8

11 WARNING This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accordance with TOs and Performance of unverified procedures may result in injury to personnel or damage to equipment. TECHNICAL ORDER VALIDATION/VERIFICATION STATUS PAGE T.O. NO. BASIC DATE CHANGE NO. DATE PTO CHANGE NO. DATE T.O 1B-52H JUN 99 CHANGE 10 1 JUL 05 AMI DATA ELEMENT DATE VALIDATED VALIDATION METHOD DATE VERIFIED VERIFICATION METHOD REMARKS (A) OAS/MIU Master Faults (F: 7-10, 2/8, PG 7-53) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 3/8, PG 7-54) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 4/8, PG 7-55) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 5/8, PG 7-56) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 6/8, PG 7-57) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 7/8, PG 7-58) 2/01/05 A OAS/MIU Master Faults (F: 7-10, 8/8, PG 7-59) 2/01/05 A CALCM Advisories (F: 7-11, 1/5, PG 7-60) 2/01/05 A CALCM Advisories (F: 7-11, 2/5, PG 7-61) 2/01/05 A CALCM Advisories (F: 7-11, 3/5, PG 7-62) 2/01/05 A CALCM Advisories (F: 7-11, 4/5, PG 7-63) 2/01/05 A CALCM Advisories (F: 7-11, 5/5, PG 7-64) 2/01/05 A CF-557, CF-558, and FRMT-7 Wpn Faults (F: 7-12, 1/2, PG 7-65) 5/16/03 A CF-557, CF-558, and FRMT-7 Wpn Faults (F: 7-12, 2/2, PG 7-66) 5/16/03 A Glossary (S, PG Glossary 1 Glossary3) 5/16/03 A (B) (B) LEGEND: (A) DATA ELEMENT: (S) = SECTION, (PG) = PAGE, (P) = PARAGRAPH, (F) = FIGURE, (T) = TABLE (B) VALIDATION OR VERIFICATION METHOD: (P) = PERFORMANCE, (S) = SIMULATION, (A) = ANALYSIS (TABLE-TOP) V/VS-9/(V/VS-10 blank)

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13 STATUS OF SAFETY AND OPERATIONAL SUPPLEMENTS T.O. 1B-52H This supplement status page is based on information available to the manual editor as of the date of this publication. The information may not be current as it must be updated by any subsequent supplement status pages and by reference to T.O. 0-1-CD-1. SUPPLEMENTS IN THIS CHANGE Number Date Short Title Section Affected SS-3 (I) 15 Mar 2004 Effects of Buffers on CALCM C/D II Weapon Navigation Solution OUTSTANDING SUPPLEMENTS Number Date Short Title Section Affected Change 9 Flyleaf-1/(Flyleaf-2 blank)

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15 table of contents page SECTION I DESCRIPTION 1-1 SECTION II NORMAL AIRCREW PROCEDURES 2-1 SECTION III EMERGENCY AIRCREW PROCEDURES 3-1 SECTION IV SUPPLEMENTARY DATA 4-1 SECTION V OPERATING LIMITATIONS 5-1 SECTION VI MISSION PLANNING 6-1 SECTION VII SYSTEMS OPERATION 7-1 GLOSSARY GLOSSARY-1 ALPHABETICAL INDEX INDEX-1 i

16 INTRODUCTION SCOPE. This manual and classified T.O. 1B-52H provide the system, procedural, and missile performance information required to operate AGM-86C Conventional ALCM (CALCM) with the CALCM Stores Management Overlay (SMO), or the AGM-86C Conventional ALCM (CALCM) and the AGM-86D CALCM Penetrator with the CALCM Penetrator Stores Management Overlay (SMO) This T.O. includes data for delivery of an AGM-86C/D air-to-surface missile under all normal and the majority of abnormal conditions. NOTE This manual will be carried aboard the aircraft when AGM-86 C/D CALCM are loaded or when AGM-86 C/D CALCM training is performed. In addition, T.O. 1B-52H will be carried when AGM-86 C/D CALCM are loaded. CONTENT. This manual contains descriptions and procedures relating to AGM-86C/D missiles and the B-52H carrier aircraft. Aircraft fuel system management with the missiles installed is given in the aircraft basic flight manuals. Aircraft performance with the pylons and missiles installed is given in the basic flight manual appendices. CHECKLISTS. Abbreviated checklists for procedures in this manual are contained in the CALCM flightcrew checklist. This checklist is identified by a TO number identical to that of this manual except for the addition of the letters CL (checklist) and a suffix number 1. ARRANGEMENT. This manual is divided into seven sections. Section I, DESCRIPTION Locates, identifies, and functionally describes the missile and aircraft components of concern to the aircrew in the delivery of an AGM-86C/D missile. Section II, NORMAL AIRCREW PROCEDURES Contains partially illustrated amplified checklists for performance of normal aircrew missile delivery and ferry procedures from preflight through after landing, procedures applicable in the event a mission is aborted, and procedures for declassifying mission data in the system. Procedures, techniques, and programming practice can be accomplished on any aircraft with OAS/AGM-86C/D equipment installed. Section III, EMERGENCY AIRCREW PROCEDURES Contains missile and pylon jettison procedures. No attempt is made to regulate or define conditions under which a mission may be aborted. Section IV, SUPPLEMENTARY DATA Contains information on operational test launch and joint test launch systems and associated procedures. Section V, OPERATING LIMITATIONS Contains important missile and weapon system limitations that must be taken into account during planning and accomplishment of a mission. Section VI, MISSION PLANNING Contains information on transportation of dangerous material, inflight emergency notification, and inflight mission data changes that can be accomplished by the flightcrew. Section VII, SYSTEMS OPERATION Contains additional material regarding the operation of the aircraft OAS/AGM-86C/D missile systems. Theory of guidance system operation, guidance performance, and malfunction analysis are included. ii Change 4

17 PRECEDENCE. Compliance with procedures herein is mandatory. In all instances, only those operations which are within the scope of the current applicable safety rules may be performed. SAFETY POLICIES. The procedures in this manual reflect the latest applicable rules and policies. Aircrew compliance with these procedures and policies is mandatory. Mission planning shall provide maximum protection to friendly and neutral areas consistent with operational requirements. Selection of launch point and type of maneuver shall be guided by the possible effect upon friendly or neutral areas of a missile guidance or control system failure. Since launch point and type of maneuver are sufficiently flexible to allow for inflight decisions, aircrews shall be briefed concerning the potential disaster hazard to friendly or neutral areas. REFERENCES. The following publications, available to using commands, should be used to gain more comprehensive information on subjects referred to in this technical order: 1B-52H-1 Flight Manual 1B-52H-1-1 Flight Manual Appendix 1, Performance Data 1B-52H-1-12 Radar Navigator s/navigator s Manual 1B-52H-1-13 Electronic Warfare Officer s Manual 1B-52H-2-31GA-1 General Aircraft/Bomb Release System B-52H 1B-52H Nonnuclear Munitions Loading Procedures 1B-52H Aircrew Weapon Delivery Manual (Nonnuclear) B-52 1B-52H Aircrew Weapon Delivery Manual (Nonnuclear) B-52/WCMD 1B-52H Aircrew Weapon Delivery Manual (Nonnuclear) B-52/JDAM 1B-52H Aircrew Weapon Delivery Manual (Nonnuclear) B-52/JSOW 1B-52H Aircrew Weapon Delivery Manual (Nonnuclear) B-52/JASSM 1B-52H Aircrew Weapon Delivery Manual (Nonnuclear) B-52/AGM-86C/D Classified Supplement 1B-52H-5 Basic Weight Checklist and Loading Data B-52H 1-1M-34 Aircrew Weapons Delivery Manual (Nonnuclear) Standard Volume JMEM Joint Munition Employment Manual SAFETY AND OPERATIONAL SUPPLEMENTS. Information involving flightcrew safety and directly pertaining to the information contained herein will be promptly forwarded to you by Safety Supplements issued against this manual. Safety Supplements covering loss of life will get to you in 48 hours by a message (called Interim Safety Supplements) and those concerning serious damage to equipment within 15 days by mail (in a formal printed form). Operational information not involving safety but of an urgent nature will be forwarded to you by Operational Supplements issued against this manual. These will be forwarded by a message (interim) or by mail (formal), depending on the urgency of the information. Interim supplements are normally replaced by formal printed supplements at an early date. Formal printed supplements are identified by red letters SS for safety supplements and black letters OS for operational supplements printed around the borders of the pages. The currency of safety and operational supplements affecting your manual can be determined by referring to the Index of Bomber Aircraft Safety Supplements (T.O. 0-1-CD-1). The title block of each supplement and the title page of this manual should also be checked to determine the effect they may have on existing supplements. You must remain constantly aware of the status of all supplements current supplements must be complied with, but there is no point in restricting your operation by complying with a replaced or rescinded supplement. As a further aid, a supplement summary is included in this manual, following the A pages, for both safety and operational supplements; however, this summary can only be as current as this manual. Safety and operational supplements will be filed in accordance with Section VI of the Air Force Technical Order System, T.O Change 10 iii

18 WARNINGS, CAUTIONS, and NOTES. The following definitions apply to Warnings, Cautions, and Notes found throughout the manual. Operating procedures, techniques, etc which could result in personal injury or loss of life if not carefully followed. Operating procedures, techniques, etc which could result in damage to equipment if not carefully followed. NOTE An operating procedure, technique,etc which is considered essential to emphasize. SHALL, WILL, SHOULD, and MAY. The following definitions apply to the words: SHALL or WILL SHOULD MAY The instructions or procedures prefaced by shall or will are mandatory. Normally used to indicate a preferred but nonmandatory method of accomplishment. An acceptable or suggested means of accomplishment. CHANGE SYMBOLS. Changes to existing material and addition of new material are indicated by one of three types of symbols determined by the nature of the material affected. Text material utilizes a vertical line in the margin adjacent to the affected area. New illustrations (figures) utilize a vertical line in the outer margin of the page. Photographs and line drawings use a miniature pointing hand to highlight the affected area. Diagrams and schematics utilize a grey tone (screening) to highlight the affected area. Change symbols are not used for blank space resulting from deletions, indexes, and tabular data where changes cannot be identified, relocation of material, or correction of minor inaccuracies unless such correction changes the meaning. RESPONSIBLE AGENCY. Every effort is made to keep this manual current. Review conferences with operating personnel and a constant review of reports assure inclusion of the latest data in this manual. Comments, corrections, and questions regarding this manual should be submitted on AF Form 847 to your local standardization/evaluation unit and routed as directed by AFI to the Flight Manual Manager, 327 BMSG/EN, Tinker AFB, Oklahoma AIRCRAFT GROUP CODING. Certain modifications which have been completed do not include all serialized aircraft in the models affected. Information pertaining to these aircraft is identified by aircraft group coding symbols such as CS. Specific aircraft serialization within these groups is identified in the appropriate flight manual under a like coding in the Aircraft Coding pages. iv Change 10

19 RETROFIT CODING. The following code symbols along with the words Less and Plus are used to distinguish information related to aircraft that have the described retrofit change incorporated from that which is applicable to aircraft not yet retrofitted. This list contains only TCTO s currently active. Those known to be completed are not included. SYMBOL T.O. NO. TITLE CS 1B-52H-753 1B-52H-756 Installation of Global Positioning System (GPS) on B-52H Aircraft (ECP 0109) Installation of Integrated Conventional Stores Management System (ICSMS) on B-52H Aircraft (ECP 0109) [AMI] 1B-52H-830 Replacement of Ballistics Computer Set AN/AYQ-10 and Inertial Navigation System AN/ASN-136 on B-52H Aircraft. Change 10 v/(vi blank)

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21 Description section I table of contents page PART 1 - B-52/CALCM SYSTEM DESCRIPTION 1-3 B-52/AGM-86 CONVENTIONAL AIR LAUNCHED CRUISE MISSILE (CALCM) WEAPON SYSTEM 1-3 B-52 CARRIER AIRCRAFT 1-3 AGM-86 MISSILE 1-3 AIRCRAFT COMMON STRATEGIC ROTARY LAUNCHER SYSTEM 1-7 PYLONS 1-7 AIRCRAFT ELECTRICAL SYSTEM 1-12 AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM (ECS/MCS) 1-12 PART 2 - B-52 AVIONICS SYSTEM 1-17 OFFENSIVE AVIONICS SYSTEM (OAS) 1-17 OFFENSIVE AVIONICS SYSTEM (OAS) INTERFACE 1-17 OAS/MISSILE SYSTEM RELATED CONTROLS AND DISPLAYS 1-17 MISSILE JETTISON 1-30 PART 3 - CALCM OAS SOFTWARE AND DISPLAYS 1-37 STORES MANAGEMENT OVERLAY (SMO) 1-37 SMO MFD DISPLAYS 1-40B RELEASE ADVISORY DISPLAYS 1-40B PRIME MISSION DATA DISPLAYS 1-40B CONTROL FUNCTION (CF) DISPLAYS 1-42 FORMAT (FRMT) DISPLAYS 1-74 SMO PROGRAM (PRGM) DISPLAY 1-83 Change /(1-2 blank)

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23 PART 1 - B-52/CALCM SYSTEM DESCRIPTION T.O. 1B-52H B-52/AGM-86 CONVENTIONAL AIR LAUNCHED CRUISE MISSILE (CALCM) WEAPON SYSTEM The B-52/CALCM weapon system consists of a B-52H carrier aircraft, two underwing six-station missile pylons, an eight-station common strategic rotary launcher (CSRL) and up to 20 AGM-86 CALCM. The full missile load may be carried for automatic or manual launch against preprogrammed targets. B-52 CARRIER AIRCRAFT The offensive avionics system (OAS) controls programming, prearming, and launching of missiles. The OAS also provides signal processing, storage avionics, control and display panels, missile supervision, regulated dc power conversion, and monitors environmental control equipment in the aircraft. The OAS interfaces with the carrier electrical sources, release circuit disconnect for pylon jettison, bomb tone scoring, and panel lighting. Primary missile control and monitor is provided through the weapon control panel (WCP) and the multifunctional displays (MFD). CALCM power control, monitoring, and launch control is provided via a Missile Interface Unit (MIU) Line Replaceable Unit (LRU) and the SMO in conjunction with existing Less [AMI] ICSMS, OAS and Global Positioning System (GPS) hardware and the Flight Management System (FMS) software; [AMI] AMI, OAS and GPS hardware, and FMS and Common Stores Processing (CSP) software. Less [AMI] The CALCM SMO executes in the B-52H Avionics Control Units (ACU) and is loaded into nonvolatile memory in the ACUs from an external load tape called the Operational Computer Program (OCP) Data Transfer Unit Cartridge (DTUC). The CALCM SMO, in conjunction with the FMS, provides the necessary CALCM weapon delivery functions for the ACU to control, monitor and release CALCM missiles utilizing existing OAS/ICSMS/GPS equipment. The SMO will only be able to operate on weapons at locations where the FMS has assigned the SMO. Even though the CALCM uses GPS for navigation, there is no GPS navigation data supplied from the aircraft GPS to the CALCM. [AMI] The CALCM SMO executes in the B-52H Avionics Control Units (ACU) and is loaded into nonvolatile memory in the ACUs from an external load cartridge called the Operational Computer Program (OCP) Data Transfer Cartridge (DTC). The CALCM SMO, in conjunction with the FMS, provides the necessary CALCM weapon delivery functions for the ACU to control, monitor and release CALCM missiles utilizing existing OAS/AMI/GPS equipment. The SMO will only be able to operate on weapons at locations where the FMS has assigned the SMO. When selected as the secondary SMO, the SMO will be limited to functions that can be performed without interfering with the operation of the primary SMO. Even though the CALCM uses GPS for navigation, there is no GPS navigation data supplied from the aircraft GPS to the CALCM. The pilot s missile controls include an ejector rack lock-unlock consent switch, a prearm-off switch, an overhead panel jettison control switch, a pylon jettison consent switch, and a pylon jettison control switch. AGM-86 MISSILE (CALCM) The AGM-86 (figure 1-1) is a subsonic, turbofan-engine powered, winged missile. The missile is designed to deliver a conventional warhead in an airto-ground mission with a very high degree of accuracy at long range. During captive flight, the missile s flight surfaces (wings, fin, elevons), and engine inlet are carried in a stowed position. After launch the missile s flight surfaces are deployed and the engine provides thrust within a few seconds. Computer controlled navigation, using a global positioning system (GPS), directs the missile to its target. AGM-86C MISSILE (CALCM C) There are two versions of the AGM-86C, the Block 0A and Block 1A missile. The Block 0A missile has a 2000 pound class warhead. The Block 1A missile has a 3000 pound class warhead. The AGM-86C missiles have the GRIU/P GPS receiver and computer co-processor supplementing the missile computer in the INE. Additionally, the AGM-86C missiles have a GPS anti-jam system. AGM-86D MISSILE (CALCM D) The AGM-86D missile has a 1000 pound class penetrator warhead. The AGM-86D also has the GRIU/P GPS receiver and computer co-processor that supplements the computer in the INE. Additionally, the missiles are outfitted with a GPS Anti-jam system. Change

24 MISSILE DIMENSIONS AND GROSS WEIGHT Length: 20 feet 9 inches Span: Wings Folded 2 feet 3 inches Wings Extended 12 feet 0 inches Approximate Gross Weight: 3267 pounds (AGM-86C) 3280 Pounds (AGM-86D) MISSILE SOFTWARE CLASSIFICATION The CALCM missile software (OFS) is secret, and as a result anytime the missile has OFS loaded it is classified as secret. There are three methods for the operator to power off the missile. All three methods overwrite the GPS crypto keys. The OFS erasure and resulting missile classification is discussed in the following paragraphs: 1) Weapon Control Panel Power Off Command - When missile power off is commanded by the WCP or CF-E commands, OAS will initiate erasure of the mission data by overwriting all mission data 1000 times. Since power will be removed after approximately 12 seconds, OAS will not complete the overwriting procedure, but the mission data will be unusable. The missile OFS is not affected by this procedure and the missile will remain SECRET. 2) Classified Data Erase Command CF When commanded OAS will initiate erasure of the mission data by overwriting all mission data 1000 times. After 180 seconds (3 minutes) erasure is complete and missile power will be removed. The missile OFS is not affected by this procedure and the missile will remain SECRET. 3) Weapon Erase Command CF-55F - When commanded OAS will initiate erasure of the mission data by overwriting all mission data 1000 times followed by erasure of the missile OFS. After 240 seconds (4 minutes) erasure will be complete and missile power will be removed. The missile OFS is erased and the missile is UNCLASSIFIED. NOTE CF-55F will erase all data from the missile, including the missile Operational Flight Software (OFS). The missile must be removed from the aircraft in order for the software to be reloaded. CF-55F will erase missile data from any selected powered missile, including when the aircraft is on the ground. MISSILE ELECTRICAL SYSTEM Missile power is furnished from the aircraft prior to and during the early part of the launch countdown. Missile battery power is initiated during launch countdown by squib activation and paralleled with carrier aircraft electronic power for approximately 2 seconds following battery activate command. All missile power is provided by the missile enginedriven generator after launch. 1-4 Change 7

25 Figure 1-1. Missile General Arrangement 1 FIN 2 ELEVON 3 TEMPERATURE PROBE COV- ER * 4 WARHEAD ARMING DEVICE SAFEING PIN 5 WING 5A HARD TARGET SMART FUZE (HTSF) ACCESS PANEL (AGM-86D) 6 ENGINE EXHAUST NOZZLE COVER 7 FUZE WELL (BLOCK 1A) 8 FUZE WELL (BLOCK 0A) 9 PAYLOAD BAY COVER 10 PITOT-STATIC PROBE COVER* *MUST BE REMOVED BY AIR- CREW Change 7 1-5

26 MISSILE GUIDANCE AND CONTROL SYSTEM The navigation/guidance system consists of the inertial navigation element (INE), radar altimeter element (RAE), flight control element (FCE), the air data element (ADE), the global positioning system (GPS) element, and in AGM-86C and AGM-86D missiles a computer co-processor (GRIU/P). The INE and GRIU/P co-processor provides a centralized processing and control function for missile flight and weapon operation. The INE receives data from the OAS before launch and inputs from the RAE, FCE, ADE, and GPS after launch. NOTE Selection of alternate as the prime navigation mode with one or both INSs operational will result in some data being transferred from the alternate nav model to the missiles which may cause a degraded launch. Inertial Navigation The inertial navigation element (INE), working in tandem with the GRIU/P co-processor in AGM-86C and AGM-86D missiles, provides control of all missile functions including navigation, guidance, autopilot, event sequencing, and warhead arming and fuzing. The INE consists of an inertial reference unit (IRU), air vehicle digital computer unit (ADCU), and a power conditioning unit (PCU). The INE is cooled by the aircraft environmental system during captive flight and the missile environmental system after launch. The IRU is an inertially stabilized platform that provides the ADCU with missile attitude reference and acceleration data for navigation computations. The ADCU within the INE and co-processor in AGM-86C and AGM-86D missiles, performs computations required for missile control, navigation, and operation. Global Positioning System (GPS) A GPS receiver is installed in the missile to aid the INE in navigation. The GPS receiver is turned on at missile power application and begins its search for the GPS satellites after launch. The GPS is not able to track the satellites until after launch due to wing shielding of the GPS antenna prior to launch. The GPS provides position and velocity inputs to the INE after the GPS begins tracking the satellites. The status of the GPS receiver cannot be monitored by the operator. The AGM-86C and AGM-86D missiles have an antijam which significantly improves the missile resistance to GPS jamming. Radar Altimeter The missile uses a cruise missile radar altimeter (CMRA) for terrain following. Air Data The air data element (ADE) measures pitot pressure and static pressure, and provides this information to the INE. MISSILE FLIGHT CONTROL SYSTEM The flight control system consists of flight control system electronics, the rate and acceleration sensors, and two elevon servos to maintain controlled flight. MISSILE ENVIRONMENTAL CONTROL SYSTEM The missile environmental control system maintains temperatures within the missile and components. Prior to launch, cooling is provided for the inertial navigation element electronics by conditioned air from the aircraft. MISSILE PROPULSION AND FUEL SYSTEM An F107 WR 100 twin spool, turbofan engine is the propulsion source for the missile. Engine start is accomplished after launch by a start cartridge. The missile fuel system is a sealed tank system using JP-10 as the missile fuel. Low pressure bleed air is provided by the engine for the missile environmental control system and fuel tank pressurization. 1-6 Change 7

27 MISSILE ARMING SYSTEM Warhead Arming Device (AGM-86C Missiles) The Warhead Arm/Disarm Device (sheet 2, figure 1-2) provides the control for the Warhead Interface Unit (WIU). A safeing pin (with streamer) is installed in the Warhead Arm/Disarm Device during ground operation (see figure 1-1). Since external access to the safeing pin is provided, there is no need to remove panels or doors. An external window allows a visual check on the status of the Warhead Arm/Disarm Device. Either an S for safe or an A for armed will be seen in the window. If the Warhead Arm/Disarm Device becomes armed during captive carry an ordnance alarm (xy ORD ALARM) will be displayed as a Missile Master Fault. On the occurrence of an ordnance alarm the OAS will send a safeing command to the Warhead Arm/Disarm Device and immediately power down the missile. Since Warhead Prearm is not an operational function of the CALCM, execution of the OAS prearm function results in the setting of an OAS software switch to satisfy the OAS launch requirements. Although the OAS provides for monitor and control of the safe circuits through the Warhead Arm/Disarm Device, the aircrew can not enable the Warhead Arm/Disarm Device; the missile computer performs this function after launch. Sheet 2, figure 1-2 illustrates the CALCM Fuzing Subsystem. At launch when the separation switch closes, pulse load power is applied to the missile computer. Closure of the separation switch also completes the main bus circuit which provides main bus power from the generator to the Warhead Arm/Disarm Device after engine start. At the selected GPS Waypoint, the missile computer will issue an Arm Enable Command which enables the Warhead Arm/Disarm Device. If the selected GPS Waypoint is Waypoint 0, the missile computer will delay 10 minutes before setting the Arm Enable Command. The Arm 1 command is issued 1 second after the Arm Enable Command. After the Arm 1 command is issued, a time delay within the WIU prevents the application of fuze power and the enabling of the Inertial/impact fuzing circuit for 35 seconds. The arm 1 command applies power to the WIU and within 5 seconds (power up time for the WIU) fuze power and turbine release are applied to each fuze. Each fuze is manually set to a 20 second arming delay time. The fuzing system is armed and ready to trigger within 25 seconds of the arm 1 command. Warhead Arming Device (AGM-86D Missiles) The Warhead Arm/Disarm Device (WAD) (sheet 3, figure 1-2) provides control and monitor interface for the Fuze Interface Unit (FIU). A safeing pin (with streamer) is installed in the WAD during ground operation (see figure 1-1). Since external access to the safeing pin is provided, there is no need to remove panels or doors. An external window allows a visual check on the status of the WAD. Either an S for safe or an A for armed will be seen in the window. If the WAD becomes armed during captive carry an ordnance alarm (xy ORD ALARM) will be displayed as a Missile Master Fault. On the occurrence of an ordnance alarm the OAS will send a safeing command to the WAD and the FIU and immediately power down the missile. Since Warhead Prearm is not an operational function of the AGM-86D, execution of the OAS prearm function results in the setting of an OAS software switch to satisfy the OAS launch requirements. Although the OAS provides for monitor and control of the safe circuits through the WAD, the aircrew can not enable the WAD; the missile computer performs this function after launch. Sheet 2 figure 1-2 illustrates the AGM-86D Fuzing System. At launch when the separation switch closes, pulse load power is applied to the missile computer. Closure of the separation switch also completes the main bus circuit that provides main load bus (MLB) from the generator to the Warhead Arm/Disarm Device after engine start. At the selected GPS way point, the inertial navigation element (INE) will issue the Arm Enable Command that applies 28VDC Main Bus Power to the Warhead Arm/Disarm Device and activates the internal motor driven rotary switch. Once the motor driven rotary switch is in the armed position it enables several electrical output pathways. The current monitor output voltage from the missile generator is routed through a set of contacts in the WAD that are interrupted by relay contacts in the motor driven rotary switch controlled by the Arm Enable signal. At the first arming waypoint the Arm enable signal is issued by the INE. This action activates the motor driven rotary switch and allows the current monitor missile generator voltage to be applied to the input of the FIU. The FIU will use the frequency content of this signal to develop appropriate arming power for the FMU-159A/B Hard Target Smart Fuze (HTSF). Change A