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Immediate Action
INTERIM CHANGE

Headquarters
Department of the Army
Washington, DC
10 January 1995

TC 1-214
Interim Change
No. I01
Expires 10 January 1997

Aircrew Training Manual

Attack Helicopter, AH-64


Justification. This interim change includes changes to Task 1004, prepare DA Form 5701-R (UH-60/AH-64 Performance Planning Card) because of revision of TM 1-1520-238-10, Operator's Manual for AH-64 Helicopter. The changes involve aircraft torque factor and engine torque factor procedures.

Expiration. This interim change expires two years from date of publication. It will be destroyed at that time unless sooner rescinded or superseded by a permanent change or revision.

1. TC 1-214, 20 May 1992, and Change 1, 10 August 1994, are changed as follows:

Page 6-21. Subparagraph 2c is superseded as follows:

Pages 6-21 through 6-27. Paragraph 3 is superseded as follows:

Step 1: Enter the torque factor chart on the left of the appropriate temperature. Move right to the ETF or ATF.

Step 2: Move vertically to the bottom of the chart, and note the torque ratio.

NOTE 1: This chart allows the pilot to determine engine performance when an aircraft is operating below +35 degrees Celsius with a less than specification (1.0) engine. For engines operating at temperatures above +35 degrees Celsius, the torque ratio equals the ETF or ATF and performance is not improved. Operating at temperatures of -15 degrees Celsius and below, all engines perform as specification engines because of the increased efficiency from the denser air.

NOTE 2: Each vertical line on the torque ration chart has a value of .002.

Step 1: Using the maximum torque available (30-minute limit) chart, enter the graph at the appropriate FAT.

Step 2: Move horizontally to PA. Then move vertically to the specification torque available.

NOTE 1: If the ATF is 1.0, enter the torque derived from step 2 above (not to exceed continuous torque limit, dual-engine) in the maximum torque available (dual-engine) block(s).

NOTE 2: If the ATF is less than 1.0, use the torque conversion chart (see Step 3 below) or multiply the specification torque by the torque ratio to determine actual torque available.

Step 3: Enter the torque conversion chart at the bottom at the specification torque available per engine %; read up until intersecting the TR (not to exceed continuous torque limit, dual-engine), and then left to the actual torque available. Record in the maximum torque available (dual engine) block(s).

NOTE: If the ETF is different for each engine, compute maximum torque available (single-engine) for each engine using the torque ratio derived from the respective engine's ETF. Do not use the ATF.

NOTE: If the ETF is different for each engine, compute the maximum continuous torque available (single-engine) for each engine using the torque ratio derived from the respective engine's ETF. Do not use the ATF.

Step 1: OGE. Using the hover ceiling maximum torque available (30-minute limit) chart, enter at PA. Move horizontally to FAT, and move vertically to read OGE gross weight.

Step 2: IGE. Using the hover ceiling maximum torque available (30-minute limit) chart, enter at PA. Move horizontally to FAT, and move vertically to read the 5-foot wheel height. Then move horizontally to read maximum gross weight IGE.

Step 1. Using the hover chart, enter at the known pressure altitude. Move right to the temperature, then draw a line down to the bottom of the lower grid.

Step 2. Enter the top left grid at maximum torque available. Move down to the desired wheel height (OGE OR IGE), and then move right to intersect the previously drawn line. Read the gross weight. This is the maximum gross weight at which the helicopter will hover.

NOTE: The use of a 10-foot power check and associated TM 1-1520-238-CL charts may be appropriate if current conditions have changed significantly.

NOTE: A change in GWT of about 200 pounds equates to a change in torque of l percent.

NOTE: If the ETF is different for each engine, compute single engine capability TAS (min/max) using maximum torque available (single-engine) derived from the lesser of the two ETFs. Do not use the ATF.

NOTE: If the ETF is different for each engine, compute the maximum allowable gross weight (single-engine) per (9) above using maximum torque available (single-engine) derived from the lesser of the two ETFs. Do not use the ATF.

NOTE 1: A change in aircraft configuration or flat plate drag, as well as use of the anti-icing system, will affect performance computations.

NOTE 2: Crew members may use approved computer programs to derive the required information during flights other than for readiness level progression and evaluation.

NOTE 3: Record "avoid" and "caution" altitudes from TM 1-1520-238-10, Chapter 9, in the Remarks section.

NOTE 4: Crew members should be aware of minimum single-engine speeds for all departure, arrival, and low-speed/low-altitude conditions.

REFERENCES:

AR 95-1
AR 95-3
FM 1-203
Task 1023
TM 1-1520-238-10
TM 1-1520-238-CL
TM 55-2840-248-23

Add pages 6-27.1 and 6-27.2 (Figure 6-6).

2. Post these changes per DA Pam 310-13.

3. File this interim change in front of the publication.

[ATZQ-ATB-ATM]

By Order of the Secretary of the Army:

GORDON R. SULLIVAN
General, United States Army
Chief of Staff

Official:

MILTON H. HAMILTON
Administrative Assistant to the
Secretary of the Army

Distribution:

Active Army, ARNG, and USAR: To be distributed in accordance with DA Form 12-11E, requirements for TC 1-214, Aircrew Training Manual, Attack Helicopter, AH-64 (Qty rqr block no. 4621).

Figure 6-6. Sample DA Form 5701-R (front)

Figure 6-7. Sample DA Form 5701-R (back)