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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 It will be destroyed at that time unless sooner rescinded or superseded by a permanent change or revision.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 Subparagraph 2c is superseded as follows:
c. Complete the items indicated by the circled numbers in figures 6-6 and 6-7 according to the instructions in TM 1-1520-238-10 and, where necessary, as supplemented below. (Items not indicated by circled numbers do not pertain to the AH-64.)
Pages 6-21 through 6-27. Paragraph 3 is superseded as follows:
3. Supplemental Instructions.
a. Departure.
(1) Item 1--Departure PA. Record the PA forecast for the time of departure.
(2) Item 2--Departure FAT. Record the FAT forecast for the time of departure.
(3) Item 3--Takeoff GWT. Record takeoff gross weight.
(4) Item 4--Load. Record the maximum anticipated weight of the load during the mission profile. (The load is the weight of expendable ordnance.)
(5) Item 5--Fuel. Record takeoff fuel weight and fuel weight required at takeoff to complete the mission.
(6) Item 6--EFT. Record the individual engine torque factors. (The ETF represents a ratio of individual engine torque available to specification torque at a reference temperature of +35 degrees Celsius. The ETF is allowed to range from 0.85 to 1.0. ETFs are located on the engine HIT log in the aircraft logbook for each engine.)
(7) Item 7--ATF. Record the aircraft torque factor. (The ATF is a ratio of individual aircraft torque available to specification torque at a reference temperature of +35 degrees Celsius. The ATF, the average of the two ETFs, is allowed to range from 0.9 to 1.0.)
(8) Item 8--TR. Torque ratio is used to compute the actual single/dual-engine maximum torque available. Follow steps 1 and 2 below.
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.
(9) Item 9--Max Torque Available (Dual Eng). Follow steps 1 through 3 below.
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).
(10) Item 10--Max Torque Available (Single Eng). Using the single-engine maximum torque available (2.5-minute limit) chart, compute the maximum single-engine torque available as shown in (9) above.
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.
(Optional. Max Continuous Torque Available (Single Eng). At the discretion of the PC, compute maximum continuous torque available (single-engine) using the maximum torque available (30-minute limit) chart as shown in (9) above. Do not exceed continuous single-engine torque limit.
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.
(11) Items 11 and 12--Max Allowable GWT (OGE/IGE).
(a) The hover ceiling maximum torque available (30-minute limit) chart is based on an ATF of 1.0. For aircraft with an ATF of 1.0, compute maximum allowable gross weight OGE/IGE using steps 1 and 2 below.
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.
(b) For aircraft with an ATF between 0.9 and 1.0, compute the maximum allowable gross weight OGE/IGE using steps 1 and 2 below.
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.
(12) Items 13 and 14--Go/No-Go Torque (OGE/IGE).
(a) OGE. Using the hover chart, enter at PA. Move horizontally to FAT, and move vertically to maximum allowable gross weight OGE (as determined in (11)(a) above). Move horizontally to the desired hover height line. Then move up to read go/no-go torque OGE.
(b) IGE. Using the hover chart, enter at PA. Move horizontally to FAT, and move vertically to maximum allowable gross weight IGE (as determined in (11)(a) above). Move horizontally to the desired hover height line. Then move up to read go/no-go torque IGE.
(13) Items 15 and 16--Predicted Hover Torque (OGE/IGE).
(a) OGE. Using the hover chart, enter at PA. Move horizontally to FAT, and move vertically to takeoff gross weight. Move horizontally to the OGE hover height line. Then move vertically to read predicted hover torque OGE.
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.
(b) IGE. Using the hover chart, enter at PA. Move horizontally to FAT, and move vertically to takeoff gross weight. Move horizontally to the desired hover height line. Then move vertically to read predicted torque at that hover height.
NOTE: A change in GWT of about 200 pounds equates to a change in torque of l percent.
b. Cruise Data.
(1) Item 17--PA. Record planned cruise PA.
(2) Item 18--FAT. Record forecast FAT at cruise altitude.
(3) Item 19--Vne KIAS. Using the airspeed operating limits chart, record the Vne.
(4) Item 20--Cruise Speed (Dual Eng IAS and TAS). Using the applicable cruise chart, record the selected cruise IAS and TAS.
(5) Item 21--Cruise Torque (Dual Eng). Using the applicable cruise chart, record the predicted dual-engine cruise torque.
(6) Item 22--Cruise Fuel Flow (Dual Eng). Using the applicable cruise chart, record the predicted dual-engine fuel flow.
(7) Item 23--Max R/C or Endurance IAS/TAS. Using the applicable cruise chart, record the maximum rate of climb or maximum indicated and true airspeed.
(8) Item 24--Max Range IAS/TAS. Using the applicable cruise chart, record the maximum range indicated and true airspeed.
(9) Items 25 and 26--Single-Eng Capability TAS (Min/Max). Select the appropriate cruise chart for PA and FAT. Enter the chart at 50 percent of the maximum single-engine torque available as determined in a (10) above. Then move vertically to the first intersection with the relevant gross weight line. Record the minimum airspeed for single-engine flight. Continue vertically to the second intersection of torque and gross weight, and record the maximum airspeed for single-engine flight. (Airspeeds should be recorded as TAS.)
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.
(10) Item 27--Max Allowable GWT (Single Eng). Using the cruise chart, select PA and FAT. Enter the chart at 50 percent of the maximum single-engine torque as determined in a (10) above. Then move up to intersect the Max R/C - Max Endurance curve. Interpolate maximum gross weight for single-engine flight.
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.
c. Fuel Management (Item 28). Use this space to record the in-flight fuel consumption check, to include fuel burnout and appropriate VFR or IFR reserve. (Task 1023 discusses fuel management procedures.)
d. Arrival.
(1) Item 29--PA. Record the forecast PA at the destination at ETA.
(2) Item 30--FAT. Record the forecast FAT at the destination at ETA.
(3) Item 31--Landing GWT. Record the estimated landing gross weight.
(4) Item 32--Torque Ratio. Using arrival environmental conditions, compute as in a(8) above.
(5) Item 33--Max Torque Available (Dual Eng). Using arrival environmental conditions, compute the maximum torque available as described in a(9) above.
(6) Item 34--Max Torque Available (Single Eng). Using arrival environmental conditions, compute the maximum single-engine torque available as described in a(10) above.
(7) Items 35 and 36--Max Allowable GWT (OGE/IGE).
(a) OGE. Using arrival environmental conditions, compute the maximum allowable gross weight OGE as described in a(11) above.
(b) IGE. Using arrival environmental conditions, compute the maximum allowable gross weight IGE as described in a(11) above.
(8) Item 37--Predicted Hover Torque (IGE). Using arrival environmental conditions and landing gross weight, compute the torque required to hover IGE as described in a(13)(b) above.
(9) Item 38--Predicted Hover Torque (OGE). Using arrival environmental conditions and landing gross weight, com-pute the torque required to hover OGE as described in a(13)(a) above.
e. Remarks (Item 39). Use these areas to record pertinent performance planning remarks.
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)