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ROUTINE

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DEPARTMENT OF THE ARMY TECHNICAL BULLETIN

CONTACT MEMORY BUTTON (CMB) INFORMATION FORAH-64A/D

Helicopter, Attack, AH-64A Apache

Helicopter, Longbow, AH-64D Apache

7300000000 (NSN 1520011069519 ) (EIC: RHA )73100000021 (NSN 1520013558250 ) (EIC: RHB)

Headquarters, Department of the Army

20 April 2007

REPORTING OF ERRORS AND RECOMMENDING IMPROVEMENTS

You can help improve this bulletin. If you find mistakes or know of a way to improve procedures, please let usknow. Mail your letter, DA Form 2028 (Recommended Changes to Publications and Blank Forms) located atthe back of this bulletin, directly to: Commander, U.S. Army Aviation and Missile Command, ATTN: AMSAM-MMC-MA-NP, Redstone Arsenal, AL 35898-5000. A reply will be furnished to you. You may also provide DAForm 2028 information to AMCOM via e-mail, fax or the World Wide Web. Our fax number is DSN 788-6546or Commercial (256) 842-6546. Our e-mail address is 2028@redstone.army.mil. Instructions for sending an

electronic 2028 may be found at the back of this bulletin immediately preceding the hard copy 2028. For theWorld Wide Web use: https://amcom2028.redstone.army.mil.

DISTRIBUTION STATEMENT C: Distribution authorized to U. S. Government agencies and their contractors only (critical technology). This determination was made on 1 December 2002. Other requestsfor this document shall be referred to: Project Manager, Apache Attack Helicopter, SFAE-AV-AAH-LI,Redstone Arsenal, AL 35898-5000.

DESTRUCTION NOTICE - Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

TABLE OF CONTENTS

Paragraph Pag

SECTION I CMB GENERAL INFORMATION

PURPOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 2CMB GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2

SECTION II REMOVING A CMB

REMOVING A CMB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3

____________*This bulletin supersedes TB 1152023820140, dated 01 JUNE 2005 including all changes

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TABLE OF CONTENTS (Cont)

Paragraph Page

SECTION III INSTALLING A CMB

INSTALLING A CMB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 3

SECTION IV CMB LOCATIONS

CMB LOCATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 6

SECTION V CMB TABLES

CMB TABLES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 116

SECTION VI ACRONYMS AND ABBREVIATIONS

Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 120

SECTION I. CMB GENERAL INFORMATION1. PURPOSE. This document contains information about Contact Memory Buttons (CMB) and procedures for in-stalling and removing CMBs. It also defines which AH-64A/D helicopter components receive CMBs.

NOTE

The aircraft components requiring maintenance management and historical data reports in this doc-ument are taken from TB 1-1500-341-01.

All components requiring CMBs are in Table 1 of this document.

2. CMB GENERAL INFORMATION.

a. Description: This section provides general background information about Contact Memory Buttons (CMB).

b. General Information: A Contact Memory Button (CMB) is a battery-free, read/write electronic data storagedevice attached to selected components tracked by the DA Form 2410. The CMB enhances configuration manage-ment, asset tracking, inspection and maintenance for the life of the component to which it is attached.

Aviation Maintenance Automated Tracking System (AMATS) is an automated system that uses CMBs to inputpart data into an existing maintenance management information system (MMIS). Data stored on the CMB is retrievedusing a CMB read/write device attached to a computer or personal digital assistant (PDA). Information is viewableand updateable on site. The retrieved information is then automatically inputted into the MMIS. Together, CMBs andan MMIS create an automated maintenance environment. After maintenance is performed on an aircraft componentand the maintenance data is entered into the MMIS, the computer or PDA is used to write the current data to thecomponents CMB.

The CMB currently in use by AMATS is part number BMEWK32, CAGE code 03BF3. This CMB, the MacSemaMiniButton is 0.11 in. high, 0.56 in. in diameter, and weighs 0.027 oz.

Figure 1. Contact Memory Button.

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SECTION II. REMOVING A CMB

3. REMOVING A CMB. This section covers removing a CMB from a component.

a. Description:

b. Initial Setup

Materials: Tools:

Dry Ice (Item 1, Table 2) Phenolic Wedge

Corrosion Preventive Compound (CPC) (Item 9, Table2)

Dry ice is solid carbon dioxide that has a temperature below -112 F (-80 C). Contact with skinwill cause serious low temperature burns. Temperature resistant gloves/apron required. Carbondioxide displaces oxygen, which can cause asphyxiation. Use only in a well ventilated area.

When removing a CMB, care should be taken not to damage the surface of the component.

c. Removing a CMB

Use dry ice to crystallize the Hysol EA 9394 that holds the CMB to the component. This can be accomplisheby applying dry ice to the CMB area for 4-5 minutes. The adhesive should become brittle.

Place an authorized blunt object, preferably a phenolic wedge, at the lip of the CMB.

Gently tap the blunt object to loosen the CMB, and eventually tap it free from the adhesive.

Any metallic surface that is exposed due to the CMB removal should be treated with the appropriate corrosionpreventative compound.

SECTION III. INSTALLING A CMB

4. INSTALLING A CMB.

a. Description: This section covers installing a CMB onto a component.

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Use all chemicals in a well-ventilated area. Refer to the Material Safety Data Sheet (MSDS) docu-ments for the chemicals for specific safe handling procedures.

Heat buildup during or after mixing Hysol EA 9394 is normal. However, do not mix quantitiesgreater than 450 grams, as dangerous heat buildup can take place, causing uncontrolled decom-

position of the mixed adhesive. As a result, toxic fumes are formed.

Use latex gloves when handling Hysol EA 9394.

Always use latex gloves during installation of CMBs to prevent contamination from oils and dirt onhands.

Hysol EA 9394 must be mixed well in order for the adhesive to bond correctly. Mix the adhesivefor several minutes until the color and consistency are uniform.

The ambient conditions during installation can affect the cure times for the adhesive. Do not install

CMBs at ambient temperatures below 50F, or the adhesive will not properly cure.

Do not apply paint, corrosion preventive compound, or adhesive over the top of the CMB. Doingso can prevent proper CMB read/write operation. If any of these substances get on the CMB, useacetone to clean the CMB, and then try reading the CMB. If the CMB cannot be read in its entirety,remove and install a new CMB in its place.

Care should be taken not to damage the metal surface of the component when preparing a com-ponent for CMB installation.

NOTE

Gather all necessary tools and materials before starting the CMB installation (See Table 2).

Refer to Figures 2 through 214 for proper placement of CMBs on components.

b. General Information: A CMB is permanently affixed to a component by Hysol EA 9394 adhesive.

c. Initial Setup

Materials:

Acetone (Item 5, Table 2) Lint-Free Cloth (Item 8, Table 2)

Latex Gloves (Item 6, Table 2) Emery Paper, 220 Grit (Item 4, Table 2)

Contact Memory Button (Item 7, Table 2) Adhesive, Hysol EA 9394 (Item 2, Table 2)

Scotch-Brite (Item 3, Table 2)

d. Installing a CMB on a component with any coated surface (paint, primer, clear coating, Pro-seal, etc.). Ref-erence paragraph 3.5 for installation of CMBs to bare metal surfaces.

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Care should be taken not to expose any bare metal.

Scuffing of the main rotor and tail rotor blades should only be done in a spanwise direction.

NOTE

Use of power tools is not permitted unless approved by RDECOM Aviation Engineering Directorate(AED).

The adhesive must form a complete bead around the outside circumference of the CMB.

(1) Clean the selected location using acetone and a lint-free cloth. Remove all oils and solids from the area

(2) Lightly scuff a inch diameter area using a Scotch-Brite pad or 220 grit emery paper. Care should betaken not to expose any bare metal. If any bare metal is exposed during scuffing, prime and paint the area. Aftethe appropriate drying time, re-scuff the area.

(3) Clean the scuffed area with acetone. Dry wipe the area with a lint-free cloth before the solvent evaporates to remove any drying residue.

(4) Allow the area to dry completely (about 5 minutes), and inspect for proper surface preparation.

(5) Lightly sand the back side of the CMB for a few seconds with 220 grit emery paper and wipe clean witha lint-free cloth to prepare the back surface for bonding.

(6) Mix the Hysol EA 9394 adhesive according to manufacturers directions.

(7) Place a small amount of Hysol EA 9394 on the back surface of the CMB.

(8) Firmly press the CMB onto the component surface, ensuring a small bead forms entirely around theCMB. Take care not to get adhesive on top of the CMB.

Make sure the CMB is safe from loading or jarring until proper handling strength of the adhesivehas been reached. Handling strength for Hysol EA 9394 will occur after 8 hours at 77 F. Only ifthe cure inspection test is passed (see 3.4.11 below), it is safe to fly the aircraft 24 hours after CMBinstallation without risk of stressing the bonded joint to the point of breaking during flight. Full curetime (7 days at 77 F or 25 C) is determined to be the time after which the adhesive has developedmaximum bond strength, maximum environmental resistance, and ultimate performance properties.

(9) Hold the CMB with your thumb until it remains where placed.

(10) Remove excess adhesive from the work area before it hardens. Use acetone for removing any unnecessary, uncured adhesive. Do not disturb the adhesive bead.

(11) To ensure proper curing of the adhesive, wait 24 hours, and test for hardness. Randomly inspect 5CMBs or 10% of CMBs, whichever is greater. Inspect this quantity/percentage for each mixed batch of adhesiveused. The test involves using yourfingernail or other object of similar hardness and applying pressure to the beadof the adhesive.

(a) If this test leaves a visible mark on the adhesive, then the adhesive is not adequately cured, andoperation of the component would introduce a possible FOD (foreign object damage) risk. The adhesive might bebad, or it could just be a little cool and thus needs more time to cure. Either remove and reinstall the CMBs (restartinat step 3.4.1) or wait and re-inspect later. If the adhesive never passes this test, then the CMBs must be removed

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and reinstalled (restarting at step 3.4.1). Either remove all CMBs installed using this mixed batch of adhesive, orremove only those for which the cure test fails (after testing 100% of the CMBs installed with this mixed batch).

(b) If no mark is left, then the adhesive has passed the cure inspection test.

(12) If touch-up paint is needed:

(a) The disturbed area must be returned to the condition stated for the component on the drawing.

(b) Mask the CMB.

(c) Apply touch-up paint around the CMB as needed.

(d) When the paint has dried, remove the masking from the CMB.

Do not scuff bare metal parts.

e. Installing a CMB on a bare metal surfaced component.

(1) Clean the selected location using acetone and a lint-free cloth. Remove all oils and solids from the area.Do not scuff bare metal parts.

(2) Follow procedures d.5 to d.11.b.

SECTION IV. CMB LOCATIONS

5. CMB LOCATIONS

a. Description: This section identifies the individual components to which CMBs are to be permanently attachedand the location of the CMB on each such component.

b. General Information: The U.S. Army has designated the individual components to which CMBs are to bepermanently attached. All such components are DA Form 2410 items, although not all DA Form 2410 items receivepermanently attached CMBs. Use the figures in this section to locate the position of the CMB on each component.

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Whenever possible, place the CMB at its designated location. Failure to do so could result in inter-ference with the full motion of the component once installed on the helicopter.

If for some reason a CMB can not be installed at the designated location, place the CMB in theadequately sized location nearest the designated location that will not interfere with moving parts

and that is accessible to read/write once installed on the helicopter.

NOTE

All components and their variations in the following figures and in Table 1 receive a CMB as long asthe component is still on the Armys active parts list. A figure within this section may only show oneof several variations of the same component due to their different part numbers.

Figure 2. Forward Inboard Engine Mount (AH-64A/D) with CMB Installed.

Figure 3. Forward Inboard Engine Mount (AH-64A/D).

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Figure 4. Wing Assembly (AH-64A/D) with CMB Installed.

Figure 5. Wing Assembly (AH-64A/D).

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Figure 6. Main Rotor Support Mast (AH-64A/D) with CMB Installed.

Figure 7. Main Rotor Support Mast (AH-64A/D).

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Figure 8. Mast Support Base (AH-64A/D) with CMB Installed.

Figure 9. Mast Support Base (AH-64A/D).

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Figure 10. Center Strut (AH-64A/D) with CMB Installed.

Figure 11. Forward and Aft Center Struts (AH-64A/D).

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Figure 12. Tail Landing Gear Shock Strut (AH-64A/D) with CMB Installed.

Figure 13. Tail Landing Gear Shock Strut (AH-64A/D) with CMB Installed.1

Figure 14. Tail Landing Gear Shock Strut (AH-64A/D).

1 Note: Option 1 shown above is the preferred location. Option 2 is an allowable location, if there is not enough available space to placethe CMB in the Option 1 location.

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Figure 15. Engine Assembly (AH-64A/D) with CMB Installed.

Figure 16. Engine Assembly (AH-64A/D).

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Figure 17. (Digital) Electrical Control Unit, (D)ECU (AH-64A/D) with CMB Installed.2

Figure 18. (Digital) Electrical Control Unit, (D)ECU (AH-64A/D).

2 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred location)but has been found to be very close to interfering with certain work fixtures for this component. If Option 2 is used, avoid having any part of theCMB (or its adhesive) on the line marked AVOID in the above phot

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Figure 19. Engine History Recorder (AH-64A/D) with CMB Installed.

Figure 20. Engine History Recorder (AH-64A/D).

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Figure 21. Main Rotor Head Assembly (AH-64A/D) with CMB Installed.

Figure 22. Main Rotor Head Assembly (AH-64A/D).

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Figure 23. Pitch Housing (AH-64A/D) with CMB Installed.

Figure 24. Pitch Housing (AH-64A/D).

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Figure 25. Lead-Lag Link (AH-64A/D) with CMB Installed.

Figure 26. Lead-Lag Link (AH-64A/D).

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Figure 27. Feathering Bearing (AH-64A/D) with CMB Installed.

Figure 28. Feathering Bearing (AH-64A/D).

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Figure 29. Lower Shoe Assembly (AH-64A/D) with CMB Installed.3

Figure 30. Lower Shoe Assembly (AH-64A/D).

3 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred location)but has been found to interfere with a restraining block in a shipping container.

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Figure 31. Damper Trunnion (AH-64A/D) with CMB Installed.

Figure 32. Damper Trunnion (AH-64A/D).

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Figure 33. Lead-Lag Damper (AH-64A/D) with CMB Installed.

Figure 34. Lead-Lag Damper (AH-64A/D).

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Figure 35. Main Rotor Blade (AH-64A/D) with CMB Installed.4

Figure 36. Main Rotor Blade (AH-64A/D).

4 Note: Option 1 shown above is the preferred location. Option 2 is an allowable location, if the two data plates are too close to one anotheto place the CMB in the Option 1 location.

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Figure 37. Main Rotor Swashplate Assembly (AH-64A/D) with CMB Installed.

Figure 38. Main Rotor Swashplate Assembly (AH-64A/D).

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Figure 39. Flight Control Arm Assembly (AH-64A/D) with CMB Installed.

Figure 40. Flight Control Arm Assembly (AH-64A/D).

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Figure 41. Main Rotor Pitch Link Assembly (AH-64A/D) with CMB Installed.

Figure 42. Main Rotor Pitch Link Assembly (AH-64A/D).

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Figure 43. Tail Rotor Head Assembly (AH-64A/D) with CMB Installed.

Figure 44. Tail Rotor Head Assembly (AH-64A/D).

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Figure 45. Tail Rotor Hub Assemblies (AH-64A/D) with CMBs Installed.

Figure 46. Tail Rotor Hub Assemblies (AH-64A/D).

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Figure 47. Tail Rotor Blade (AH-64A/D) with CMB Installed.5

Figure 48. Tail Rotor Blade (AH-64A/D).

5 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred locationbut has been found to interfere with the leading edge erosion guard currently being installed on AH-64 tail rotor blades.

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Figure 49. Tail Rotor Swashplate (AH-64A/D) with CMB Installed.6

Figure 50. Tail Rotor Swashplate (AH-64A/D).

6 .Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location. If there is not enough available spaceto install CMB in Option 1 location

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Figure 51. Main Transmission Assembly (AH-64A/D) with CMB Installed.

Figure 52. Main Transmission Assembly (AH-64A/D).

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Figure 53. Main Rotor Drive Plate Assembly (AH-64A/D) with CMB Installed.

Figure 54. Main Rotor Drive Plate Assembly (AH-64A/D).

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Figure 55. Nose Gearbox Assembly, Left (AH-64A/D) with CMB Installed.7

Figure 56. Nose Gearbox Assembly, Left (AH-64A/D).

Figure 57. Nose Gearbox Assembly, Right (AH-64A/D).

7 Note: Option 1 and Option 2 shown above are equally preferred locations. Place the CMB beside the data plate on the side with the mosavailable space.

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Figure 58. Intermediate Gearbox Assembly (AH-64A/D) with CMB Installed.

Figure 59. Intermediate Gearbox Assembly (AH-64A/D).

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Figure 60. Tail Rotor Gearbox (AH-64A/D) with CMB Installed.

Figure 61. Tail Rotor Gearbox (AH-64A/D).

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Figure 62. Forward Hanger Bearing (AH-64A/D) with CMB Installed.

Figure 63. Forward Hanger Bearing (AH-64A/D).

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Figure 64. Aft Hanger Bearing Assembly (AH-64A/D) with CMB Installed.

Figure 65. Aft Hanger Bearing Assembly (AH-64A/D).

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Figure 66. Hydraulic Pump, Primary/Utility (AH-64A/D) with CMB Installed.

Figure 67. Hydraulic Pump, Primary and Utility (AH-64A/D).

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Figure 68. Hydraulic Manifold, Utility (AH-64A/D) with CMB Installed.

Figure 69. Hydraulic Manifold, Utility (AH-64A/D).

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Figure 70. Engine Starter (AH-64A/D) with CMB Installed.

Figure 71. Engine Starter (AH-64A/D).

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Figure 72. Generator Assembly (AH-64A/D) with CMB Installed.

Figure 73. Generator Assembly (AH-64A/D).

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Figure 74. Fuel Transfer Pump (AH-64A/D) with CMB Installed.

Figure 75. Fuel Transfer Pump (AH-64A/D).

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Figure 76. Fuel Crossfeed Valve (AH-64A/D) with CMB Installed.

Figure 77. Fuel Crossfeed Valve (AH-64A/D).

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Figure 78. Nitrogen Inerting Unit (AH-64A/D) with CMB Installed.

Figure 79. Nitrogen Inerting Unit (AH-64A/D).

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Figure 80. Collective Servo Support (AH-64A/D) with CMB Installed.

Figure 81. Collective Servo Support (AH-64A/D).

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Figure 82. Longitudinal Servo Support (AH-64A/D) with CMB Installed.

Figure 83. Longitudinal Servo Support (AH-64A/D).

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Figure 84. Lateral Servo Support (AH-64A/D) with CMB Installed.

Figure 85. Lateral Servo Support (AH-64A/D).

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Figure 86. Forward Longitudinal Bellcrank Assembly (AH-64A/D) with CMB Installed.

Figure 87. Forward Longitudinal Bellcrank Assembly (AH-64A/D).

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Figure 88. Longitudinal Torque Link Assembly (AH-64A/D) with CMB Installed.

Figure 89. Longitudinal Torque Link Assembly (AH-64A/D).

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Figure 90. Longitudinal Link (AH-64A/D) with CMB Installed

Figure 91. Longitudinal Link (AH-64A/D).

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Figure 92. Aft Longitudinal Bellcrank Assembly (AH-64A/D) with CMB Installed.

Figure 93. Aft Longitudinal Bellcrank Assembly (AH-64A/D).

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Figure 94. Collective Bellcrank (AH-64A/D) with CMB Installed.

Figure 95. Collective Bellcrank (AH-64A/D).

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Figure 96. Actuators, Electro-Mech (AH-64A/D) with CMBs Installed.8

8 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred locationbut has been found to interfere with data labels on some actuators (as shown above).

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Figure 97. Actuators, Electro-Mech (AH-64A/D) with CMBs Installed.

Figure 98. Actuators, Electro-Mech (AH-64A/D).

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Figure 99. Mixer Support Assembly (AH-64A/D) with CMB Installed.

Figure 100. Mixer Support Assembly (AH-64A/D).

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Figure 101. DASE Computer (AH-64A) with CMB Installed.

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Figure 102. DASE Computer (AH-64A).

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Figure 103. Environmental Control Unit (AH-64A) with CMB Installed.

Figure 104. Environmental Control Unit (AH-64A).

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Figure 105. Auxiliary Power Unit (AH-64A) CMB Location.

Figure 106. Auxiliary Power Unit (AH-64A).

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Figure 107. Auxiliary Power Unit (AH-64D) with CMB Installed.

Figure 108. Auxiliary Power Unit (AH-64D).

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Figure 109. APU PTO Clutch (AH-64A/D) with CMB Installed.

Figure 110. APU PTO Clutch, COSSI (AH-64A/D) with CMB Installed.

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Figure 111. APU PTO Clutch (AH-64A/D).

Figure 112. APU PTO Clutch, COSSI (AH-64A/D).

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Figure 113. Signal Data Converter (AH-64A) with CMB Installed.

Figure 114. Signal Data Converter (AH-64A).

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Figure 115. Inertial Navigation System (AH-64A) CMB Location.

Figure 116. Inertial Navigation System (AH-64D) with CMB Installed.

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Figure 117. Inertial Navigation System (AH-64A/D).

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Figure 118. Improved Data Modem (AH-64D) with CMB Installed.

Figure 119. Improved Data Modem (AH-64D).

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Figure 120. Wing Pylon Actuator (AH-64A/D) with CMB Installed.

Figure 121. Wing Pylon Actuator (AH-64A/D).

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Figure 122. Fire Control Computer (AH-64A) with CMB Installed.9

Figure 123. Fire Control Computer (AH-64A; ACY on left, ACZ on right).

9 Note: The CMB location is identical on the ACY and ACZ versions. Therefore a photo of only one version is given.

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Figure 124. Omnidirectional Airspeed Sensor (AH-64A) with CMB Installed.

Figure 125. Omnidirectional Airspeed Sensor (AH-64A).

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Figure 126. Air Data Processor (AH-64A) with CMB Installed.

Figure 127. Air Data Processor (AH-64A).

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Figure 128. Power Dist M/R De-Icer (AH-64A) with CMB Installed.

Figure 129. Power Dist M/R De-Icer (AH-64A).

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Figure 130. Remote Hellfire Electronics (RHE) Unit (AH-64A) with CMB Installed.

Figure 131. Remote Hellfire Electronics (RHE) Unit (AH-64A).

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Figure 132. TADS Electronic Unit (AH-64A/D) CMB Location.

Figure 133. TADS Electronic Unit (AH-64A/D).

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Figure 134. Laser Electronic Unit (AH-64A/D) CMB Location.

Figure 135. Laser Electronic Unit (AH-64A/D).

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Figure 136. TADS Power Supply (AH-64A/D) CMB Location.

Figure 137. TADS Power Supply (AH-64A/D).

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Figure 138. TADS Turret (AH-64A/D) CMB Location.

Figure 139. TADS Turret (AH-64A/D).

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Figure 140. Environmental Control System (AH-64A/D) CMB Location.

Figure 141. Environmental Control System (AH-64A/D) CMB Location.10

10 Note: Option 1 shown above is the preferred location. Option 2 is an allowable location, if there is not enough available space to placethe CMB in the Option 1 location.

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Figure 142. Environmental Control System (AH-64A/D).

Figure 143. TADS Servo Electronic Torque Amplifier (AH-64A/D) with CMB Installed.

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Figure 144. TADS Servo Electronic Torque Amplifier (AH-64A/D) with CMB Installed.11

Figure 145. TADS Servo Electronic Torque Amplifier (AH-64A/D).

11 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred locationbut has been found to interfere with a label on some parts (as shown in the top photo).

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Figure 146. Boresight Assembly (AH-64A/D) CMB Location.

Figure 147. Boresight Assembly (AH-64A/D).

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Figure 148. Night Shroud Assembly (AH-64A/D) CMB Location.

Figure 149. Night Shroud Assembly (AH-64A/D).

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Figure 150. Night Sensor (AH-64A/D) with CMB Installed.

Figure 151. Night Sensor (AH-64A/D).

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Figure 152. Day Shroud Assembly (AH-64A/D) CMB Location.

Figure 153. Day Shroud Assembly (AH-64A/D).

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Figure 154. Day Sensor Sub-Assembly (AH-64A/D) CMB Location.

Figure 155. Day Sensor Sub-Assembly (AH-64A/D) with CMB Installed.12

12 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred location)but is on a part that may be replaced during component repair.

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Figure 156. Day Sensor Sub-Assembly (AH-64A/D).

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Figure 157. Laser Transceiver (AH-64A/D) CMB Location.

Figure 158. Laser Transceiver (AH-64A/D).

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Figure 159. Laser Tracker/Receiver (AH-64A/D) CMB Location.

Figure 160. Laser Tracker/Receiver (AH-64A/D).

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Figure 161. TV Sensor (AH-64A/D) with CMB Installed.

Figure 162. TV Sensor (AH-64A/D).

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Figure 163. Control Panel (AH-64A/D) with CMB Installed.13

Figure 164. Control Panel (AH-64A/D) CMB Location.

13 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred locationbut has been found to interfere with removal of a cover/panel from the assembly.

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Figure 165. Control Panel (AH-64A/D).

Figure 166. Optical Relay Column (AH-64A/D) CMB Location.

Figure 167. Optical Relay Column (AH-64A/D).

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Figure 168. IVD HDD (AH-64A/D) CMB Location.

Figure 169. IVD HDD (AH-64A/D).

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Figure 170. Left Hand Grip (AH-64A/D) CMB Location.

Figure 171. Right Hand Grip (AH-64A/D) CMB Location.

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Figure 172. Left Hand & Right Hand Grips (AH-64A/D).

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Figure 173. Alphanumeric Display (AH-64A/D) with CMB Installed.

Figure 174. Alphanumeric Display (AH-64A/D) CMB Location.14

14 Note: Option 1 shown above is the current preferred location. Option 2 is an allowable location (and was previously the preferred location)but is on a bracket that may be replaced during component repair.

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Figure 175. Alphanumeric Display (AH-64A/D).

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Figure 178. TEDAC Power Supply Module (AH-64A/D) with CMB Installed.

Figure 179. TEDAC Power Supply Module (AH-64A/D).

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Figure 180. TEDAC Video Electronics Module (AH-64A/D) with CMB Installed.

Figure 181. TEDAC Video Electronics Module (AH-64A/D).

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Figure 182. TEDAC Display Unit (AH-64A/D) with CMB Installed.

Figure 183. TEDAC Display Unit (AH-64A/D).

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Figure 184. PNVS Turret (AH-64A/D) with CMB Installed.

Figure 185. PNVS Turret (AH-64A/D).

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Figure 186. Azimuth Gimbal Assembly (AH-64A/D) CMB Location.

Figure 187. Azimuth Gimbal Assembly (AH-64A/D).

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Figure 188. PNVS Shroud Assy (AH-64A/D) CMB Location.

Figure 189. PNVS Shroud Assembly (AH-64A/D).

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Figure 190. PNVS Electronic Control Amp Assembly (AH-64A/D) CMB Location.15

15 Note: Option 1 shown above is the preferred location. Option 2 is an allowable location (and was previously the preferred location) but iless easily accessed with a CMB read/write device when the component is installed.

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Figure 191. PNVS Electronic Control Amp Assembly (AH-64A/D).

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Figure 192. PNVS Electronic Unit (AH-64A/D) CMB Location.

Figure 193. PNVS Electronic Unit (AH-64A/D).

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Figure 194. Azimuth Drive Assembly (AH-64A/D) with CMB Installed

Figure 195. Azimuth Drive Assembly (AH-64A/D).

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Figure 196. Derotation Unit Assembly (AH-64D) with CMB Installed.16

Figure 197. Derotation Unit Assembly (AH-64D).

16 Note: This components 2410 reporting requirement was dropped in April 2004. Therefore, CMB installations on this component have ceasedThere is, however, no requirement to remove a previously

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Figure 198. Symbol Generator (AH-64A) with CMB Installed.

Figure 199. Symbol Generator (AH-64A).

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Figure 200. Display Processor, Left (AH-64D) with CMB Installed.

Figure 201. Display Processor, Right (AH-64D) with CMB Installed.

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Figure 202. Display Processor (AH-64D).

Figure 203. IHADSS Sight Electronic Unit (AH-64A/D) with CMB Installed.

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Figure 204. IHADSS Sight Electronic Unit (AH-64A/D).

Figure 205. IHADSS Display Electronic Unit (AH-64A/D) with CMB Installed.

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Figure 206. IHADSS Display Electronic Unit (AH-64A/D).

Figure 207. Comparator/Processor (AH-64A/D) with CMB Installed.

Figure 208. Comparator/Processor (AH-64A/D).

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Figure 209. Laser Sensor Unit (AH-64A/D) with CMB Installed.

Figure 210. Laser Sensor Unit (AH-64A/D).

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Figure 211. Comparator (AH-64A/D) with CMB Installed.

Figure 212. Comparator (AH-64A/D).

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Figure 213. Countermeasure Transmitter (AH-64A/D) with CMB Installed.

Figure 214. Countermeasure Transmitter (AH-64A/D).

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SECTION V. CMB TABLES

6. CMB TABLES.

a. Description: This section includes tables that identify the components on which CMBs are to be installed

and the expendable supplies used to install CMBs.

b. General Information: The U.S. Army has designated the individual components on which CMBs are to beinstalled. All such components are DA Form 2410 items. Table 1 contains all AH-64 components that require aCMB. Also, use Table 2 to identify the expendable supplies used to install CMBs.

NOTE

The aircraft components requiring maintenance management and historical data reports in this sec-tion are taken from TB 1-1500-341-01.

Table 1. Components Requiring CMBs

ITEM1 WUC2FIG-URE(S)

ENG MOUNT SPT FWD INBD 02B10N 2, 3

WING ASSY L 02B18A 4, 5

WING ASSY RH 02B18B 4, 5

MAST, M/R SUPPORT 02B27 6, 7

BASE ASSY MAST SUPPORT 02B28 8, 9

STRUT FWD CENTER LH 02B29A 10, 11

STRUT FWD CENTER RH 02B29B 10, 11

STRUT AFT CENTER LH 02B31A 10, 11

STRUT AFT CENTER RH 02B31B 10, 11

SHOCK STRUT ASSY (Tail) 03B01 12-14

T700-GE-701C ENGINE ASSY 04A 15, 16

T700-GE-701 ENGINE ASSY 04A 15, 16

ELECTRICAL CONTROL UNIT 04A06A 17, 18

HISTORY RECORDER 04A06B 19, 20

MAIN ROTOR HEAD ASSY 05A01 21, 22

PITCH HOUSING 05A01I 23, 24

LEAD LAG LINK ASSY 05A01I01 25, 26

FEATHERING BEARING 05A01I02 27, 28

LOWER SHOE ASSY 05A01V 29, 30

TRUNNION, DAMPER 05A01W 31, 32

LEAD LAG DAMPER 05A01Z 33, 34

MAIN ROTOR BLADE 05A02 35, 36

M/R SWASHPLATE ASSY 05A03A 37, 38

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Table 1. Components Requiring CMBs Continued

ITEM1

WUC2 FIG-

URE(S)

ARM ASSY, FLIGHT CONT 05A03B01 39, 40

M/R PITCH LINK ASSY 05A03C 41, 42

TAIL ROTOR HEAD ASSY 05B01 43, 44

TAIL ROTOR HUB ASSY 05B01P 45, 46

TAIL ROTOR BLADE ASSY 05B02 47, 48

T/R SWASHPLATE ASSY 05B03A 49, 50

MAIN TRANSMISSION ASSY 06A 51, 52

MAIN ROTOR DRIVE PLATE 06A08 53, 54

NOSE GEARBOX ASSY RH and LH 06E 55-57

INTERMEDIATE GEARBOX ASSY 06F 58, 59

TAIL ROTOR GEARBOX ASSY 06G01 60, 61

HANGER BEARING FWD 06H18C 62, 63

HANGER BEARING AFT 06H18D 64, 65

HYDRAULIC PUMP (PRIMARY) 07A01 66, 67

HYDRAULIC PUMP (UTILITY) 07B01 66, 67

MANIFOLD, HYDRAULIC (Utility) 07B05 68, 69

ENGINE STARTER 07D01 70, 71

GENERATOR 09A01 72, 73

PUMP, SUBMERGED FUEL 10C 74, 75

VALVE ASSY, CROSSFEED FUEL 10M01 76, 77NITROGEN INERTING UNIT 10P 78, 79

COLL ACTUATOR SPT ASSY 11D01C01 80, 81

LONG ACTUATOR SUPPORT 11D01D01 82, 83

LATERAL ACTUATOR SPT ASSY 11D01E01 84, 85

FWD LONGITUDE BELLCRANK 11D15 86, 87

LONG TORQUE LINK ASSY 11D18 88, 89

LONGITUDINAL LINK 11D20 90, 91

AFT LONGITUDE BELLCRANK 11D21 92, 93

COLLECTIVE BELLCRANK 11D24 94, 95

ACTUATOR, ELECTRO-MECH (Stabilator) 11D25 96-98

SUPPORT ASSY, MIXER 11D27 99, 100

DASE COMPUTER 11H01 101, 102

ENVIRONMENTAL CONTROL UNIT 13A 103, 104

AUXILIARY POWER UNIT 15B 105-108

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Table 1. Components Requiring CMBs Continued

ITEM1

WUC2

FIG-URE(S)

APU PTO CLUTCH 15B05 109-112

SIGNAL DATA CONVERTER 19E04B 113-114

INS 19E04E 115-117

IMPROVED DATA MODEM 19V01 118, 119

WING PYLON ACTUATOR 30A01A02 120, 121

FIRE CONTROL COMPUTER 31A 122, 123

OMNI-DIRECTIONAL SENSOR 31B01 124, 125

AIR DATA PROCESSOR 31B02 126, 127

POWER DIST M/R DE-ICER 31B11 128, 129

R H E UNIT 32A 130, 131

TADS SYSTEM 33

TADS ELECTRONIC UNIT 33A 132, 133

LASER ELECTRONIC UNIT 33B 134, 135

TADS POWER SUPPLY 33C 136, 137

TADS TURRET 33D 138, 139

ENVIRONMENTAL CONTROL SYS 33D02 140-142

TADS SERVO ELEC/TORQ AMP 33D03 143-145

BORESIGHT ASSY 33D04 146, 147

NIGHT SHROUD ASSY 33D05 148, 149

NIGHT SENSOR 33D06 150, 151

DAY SHROUD ASSY 33D08 152, 153

DAY SENSOR SUB-ASSY 33D09 154-156

LASER XCVR 33D09A 157, 158

LASER TRACKER RCVR 33D09C 159, 160

T.V. SENSOR 33D09D 161, 162

CONTROL PANEL 33E01 163-165

OPTICAL RELAY COLUMN 33E02 166, 167

IVD HDD 33E03 168, 169

LEFT HAND GRIP 33E04 170, 172

RIGHT HAND GRIP 33E05 171, 172

ALPHANUMERIC DISPLAY 33E06 173-175

TEDAC 33F

TEDAC SUB-ASSY 33F01 176, 177

TEDAC POWER SUPPLY MODULE 33F02 178, 179

TEDAC VIDEO ELEC MODULE 33F04 180, 181

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Table 1. Components Requiring CMBs Continued

ITEM1

WUC2 FIG-

URE(S)

TEDAC DISPLAY UNIT 33F05 182, 183

PNVS SYSTEM 34

PNVS TURRET 34A 184, 185

AZ GIMBAL ASSY 34A02 186, 187

PNVS SHROUD ASSY 34A03 188, 189

PNVS ELEC CTRL AMP ASSY 34B 190, 191

PNVS ELECTRONIC UNIT 34C 192, 193

AZIMUTH DRIVE ASSY 35B02C 194, 195

DEROTATION UNIT 37A11 196, 197

SYMBOL GENERATOR 38A 198, 199

DISPLAY PROCESSOR 38A 200-202

IHADSS SIGHT ELECT UNIT 39B 203, 204

IHADSS DISPLAY ELECT UNIT 39C 205, 206

COMPARATOR/PROCESSOR 76A03 207, 208

LASER SENSOR UNIT 76E01 209, 210

COMPARATOR ASSY 76E02 211, 212

COUNTERMEASURE XMTR 76F01 213, 214

ITEM1

: The nomenclature of the DA Form 2410 item. Subassemblies are identified by indention under the nexthigher assembly. For DA Form 2410 item part numbers and national stock numbers associated with each

item, refer to TB 1-1500-341-01.

WUC2

: Table 1 is sorted by item Work Unit Code (WUC). The WUC identifies a component without regard topossible part numbers or NSNs.

WUC

02 Airframe 13 Environmental Control 35 Area Weapons Sys

03 Landing Gear 14 Hoists and Winches 36 Other Weapons Sys

04 Power Plant 15 Auxiliary Power Unit 37 Fire Control/Radar

05 Rotor System 16 Mission Equipment 38 Symbol Generation

06 Drive System 17 Emergency Equipment 39 IHADSS07 Hydraulics/Pneudraulics 19 Avionics 52 Auto Pilot System

08 Instrument System 30 Armament Sub System 76 Electronics Countermeasures

09 Electrical Installation 31 Fire Control Sub Sys 80 Special Tools

10 Fuel System 32 Hellfire Sub System 82 Flyaway Items

11 Flight Control System 33 TADS Assembly 83 Ground Support Sys

12 Utility System 34 PNVS Assembly

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Table 2. CMB Expendable Supplies and Materials

ItemNumber

NSN/ CAGEC (optional) Description U/M

1 6830-00-247-0619 Dry Ice LB

2 8040-01-169-5304 Adhesive, Hysol EA 9394 KT

2.1 8040-01-288-5856 Alternate Adhesive, Hysol EA 9394 Qt. KT

3 5330-01-197-7789 Scotch-Brite EA

4 5350-00-224-7209 Paper, abrasive, 220 grit SH

5 6810-00-223-2739 Acetone 1 Qt.Can

6 6515-01-149-8841 Latex Gloves PR

7 None/ 64928 CMB KIT 3009DD (Symbol Technologies) EA

Contains Contact Memory Buttons P/N BMEWK32

(5 packets of CMBs of 100 each) and CMB Mount

Adhesive Tape P/N DS9096P (1 roll of 500 each)8 None/ 33591 Lint-Free Towels 75260 (Kimberly-Clark Corp) BX

Contains 200 one-ply towels 10" x 13" per box

9 8030-00-244-1297 Compound, Corrosion Preventive, MIL-C-16173, Gr 2

1 Qt.Can

SECTION VI. ACRONYMS AND ABBREVIATIONS

7. Acronyms and Abbreviations

a. Description: This section identifies the acronyms and abbreviations used within this document.

b. General Information: The U.S. Army has designated the acronyms used in this document.

Table 3.

AMATS Aviation Maintenance Automated Tracking System

APU Auxiliary Power Unit

AZ Azimuth

CMB Contact Memory Button

COLL Collective

COSSI Commercial Operations and Support Savings Initiative

CPC Corrosion Preventive Compound

DASE Digital Automated Stabilization Equipment

DECU Digital Electrical Control Unit

DIST Distribution

ECS Environmental Control System

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Table 3. Continued

ELEC Electronic

ENG Engine

ENVR CONT Environmental Control

FWD ForwardIHADSS Integrated Helmet and Display Sight System

INBD Inboard

INS Inertial Navigation System

IVD HDD Indirect View Display Heads Down Display

LAT ACT Lateral Actuator

LEU Laser Electronic Unit

LH Left Hand

M/R Main Rotor

MSDS Material Safety Data Sheet

NSN National Stock Number

P/N Part Number

PNVS Pilot Night Vision Sensor

PTO Power Take-Off

RCVR Receiver

RH Right Hand

RHE Remote Hellfire Electronics

SPT Support

STG Stage

SYS System

TADS Target Acquisition Designation Sight

TEDAC TADS Electronic Display and Control

T/R Tail Rotor

T.V. Television

WUC Work Unit Code

XCVR Transceiver

XMTR Transmitter

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By Order of the Secretary of the Army

GEORGE W. CASEY, JR.General, United States Army

Chief of StaffOfficial:

JOYCE E. MORROWAdministrative Assistant to the

Secretary of the Army0710001

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These are the instructions for sending an electronic 2028

The following format must be used if submitting an electronic 2028. The subject line must beexactly the same and all fields must be included; however only the following fields aremandatory: 1, 3, 4, 5, 6, 7, 8, 9, 10, 13, 15, 16, 17, and 27.

From: Whomever To: 2028@redstone.army.mil

Subject: DA Form 2028

1. From:Joe Smith2. Unit:home

3. Address:4300 Park

4. City:Hometown

5. St:MO

6. Zip:77777

7. Date Sent:19--OCT--93

8. Pub no: 55--2840--229--23

9. Pub Title: TM

10. Publication Date:04--JUL--85

11. Change Number: 7

12. Submitter Rank: MSG13. Submitter FName: Joe

14. Submitter MName: T

15. Submitter LName: Smith

16. Submitter Phone: 123--123--1234

17. Problem:1

18. Page: 2

19. Paragraph: 3

20. Line: 4

21. NSN: 5

22. Reference: 6

23. Figure: 7

24. Table: 825. Item:9

26. Total: 123

27. Text:This is the text for the problem below line 27.

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RECOMMENDED CHANGES TO PUBLICATIONS AND

BLANK FORMS

For use of this form, see AR 25--30; the proponent agency is ODISC4.

Use Part II (reverse) for Repair Parts and Spe-cial Tool Lists (RPSTL) and Supply Catalogs/Supply Manuals (SC/SM)

DATE

8/30/02

TO: (Forward to proponent of publication or form)(Include ZIP Code)

Commander, U.S. Army Aviation and Missile Command

ATTN: AMSAM--MMC--MA--NP

Redstone Arsenal, 35898

FROM: (Activity and location)(Include ZIP Code)

MSG, Jane Q. Doe

1234 Any Street

Nowhere Town, AL 34565

PART 1 -- ALL PUBLICATIONS (EXCEPT RPSTL AND SC/SM) AND BLANK FORMS

PUBLICATION/FORM NUMBER

TM 9--1005--433--24

DATE

16 Sep 2002

TITLE Organizational, Direct Support, And GeneralSupport Maintenance Manual for Machine Gun, .50Caliber M3P and M3P Machine Gun Electrical Test SetUsed On Avenger Air Defense Weapon System

ITEM

NO.

PAGE

NO.

PARA--

GRAPH

LINE

NO. *

FIGURE

NO.

TABLE

NO.RECOMMENDED CHANGES AND REASON

1 WP0005

PG 3

2 Test or Corrective Action column should identify a different WP number.

* Reference to line numbers within the paragraph or subparagraph.

TYPED NAME, GRADE OR TITLE

MSG, Jane Q. Doe, SFC

TELEPHONE EXCHANGE/AUTOVON, PLUS EXTEN-SION

788--1234

SIGNATURE

DA FORM 2028, FEB 74 REPLACES DA FORM 2028, 1 DEC 68, WHICH WILL BE USED. USAPA V3.01

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TO: (Forward direct to addressee listed in publication)

Commander, U.S. Army Aviation and Missile Command

ATTN: AMSAM--MMC--MA--NP

Redstone Arsenal, 35898

FROM: (Activity and location) (Include ZIP Code)

MSG, Jane Q. Doe

1234 Any Street

Nowhere Town, AL 34565

DATE

8/30/02

PART II -- REPAIR PARTS AND SPECIAL TOOL LISTS AND SUPPLY CATALOGS/SUPPLY MANUALS

PUBLICATION NUMBER DATE TITLE

PAGE

NO.

COLM

NO.

LINE

NO.

NATIONAL STOCK

NUMBER

REFERENCE

NO.

FIGURE

NO.

ITEM

NO.

TOTAL NO.OF MAJOR

ITEMSSUPPORTED

RECOMMENDED ACTION

PART III -- REMARKS (Any general remarks or recommendations, or suggestions for improvement of publications and

blank forms. Additional blank sheets may be used if more space is needed.)

TYPED NAME, GRADE OR TITLE

MSG, Jane Q. Doe, SFC

TELEPHONE EXCHANGE/AUTOVON,PLUS EXTENSION

788--1234

SIGNATURE

USAPA V3.01

8/4/2019 TB 1-1520-238-20-140

129/130

RECOMMENDED CHANGES TO PUBLICATIONS AND

BLANK FORMS

For use of this form, see AR 25--30; the proponent agency is ODISC4.

Use Part II (reverse) for Repair Parts and Spe-cial Tool Lists (RPSTL) and Supply Catalogs/Supply Manuals (SC/SM)

DATE

TO: (Forward to proponent of publication or form)(Include ZIP Code) FROM: (Activity and location)(Include ZIP Code)

PART 1 -- ALL PUBLICATIONS (EXCEPT RPSTL AND SC/SM) AND BLANK FORMS

PUBLICATION/FORM NUMBER DATE TITLE

ITEM

NO.

PAGE

NO.

PARA--

GRAPH

LINE

NO. *

FIGURE

NO.

TABLE

NO.RECOMMENDED CHANGES AND REASON

* Reference to line numbers within the paragraph or subparagraph.

TYPED NAME, GRADE OR TITLE TELEPHONE EXCHANGE/AUTOVON, PLUS EXTEN-SION

SIGNATURE

DA FORM 2028, FEB 74 REPLACES DA FORM 2028, 1 DEC 68, WHICH WILL BE USED. USAPA V3.01

Commander, U.S. Army Aviation and Missile Command

ATTN: AMSAM-MMC-MA-NP

Redstone Arsenal, AL 35898

8/4/2019 TB 1-1520-238-20-140

130/130

TO: (Forward direct to addressee listed in publication) FROM: (Activity and location) (Include ZIP Code) DATE

PART II -- REPAIR PARTS AND SPECIAL TOOL LISTS AND SUPPLY CATALOGS/SUPPLY MANUALS

PUBLICATION NUMBER DATE TITLE

PAGE

NO.

COLM

NO.

LINE

NO.

NATIONAL STOCK

NUMBER

REFERENCE

NO.

FIGURE

NO.

ITEM

NO.

TOTAL NO.OF MAJOR

ITEMSSUPPORTED

RECOMMENDED ACTION

PART III -- REMARKS (Any general remarks or recommendations, or suggestions for improvement of publications and

blank forms. Additional blank sheets may be used if more space is needed.)

Commander, U.S. Army Aviation and Missile Command

ATTN: AMSAM-MMC-MA-NP

Redstone Arsenal, AL 35898