C1, TC 1-212
Change 1 HEADQUARTERS
DEPARTMENT OF THE ARMY
Washington, DC, 23 December 2002
AIRCREW TRAINING MANUAL
UTILITY HELICOPTER, UH-60/EH-60
1. Change TC 1-212, 8 March 1996, as follows.
Remove old pages Insert new pages
v and vi v and vi
6-19 through 6-26 6-19 through 6-26.18
Glossary-1 through Glossary-12 Glossary-1 through Glossary-12
Reference-1 through Reference-8 Reference-1 through Reference-8
Index-1 through Index-8 Index-1 through Index-8
DA Form 5701-R, Sep 92 DA Form 5703-R, UH-60 Performance
UH-60/AH-64 Performance Planning Card (Front)
Planning Card (PPC) (Front)
DA Form 5701-R, Sep 92 DA Form 5703-R, UH-60 Performance
UH-60/AH-64 Performance Planning Card (Back)
Planning Card (PPC) (Back)
2. A star ê marks new or changed material.
3. File this transmittal sheet in the front of the publication.
4. The effective date of Change 1 is 15 January 2003.
DISTRIBUTION RESTRICTION: Approved for public release; distribution is unlisted.
By Order of the Secretary of the Army:
ERIC K. SHINSEKI
General, United States Army
Chief of Staff
Official:
JOEL B. HUDSON
Administrative Assistant to the
Secretary of the Army
0220011
DISTRIBUTION:
Active Army, Army National Guard, and U. S. Army Reserve: To be distributed in accordance
with the initial distribution number 113889, requirements for TC 1-212.
TC 1-212
v
Task 2130 Load, secure, and unload litter and ambulatory
patients .................................................................................................. Appendix A-3
Task 2131 Identify and treat adverse effects of altitude on a patient
with chest and/or head injuries ................................................................. Appendix A-5
Task 2132 Perform a preflight inspection of medical equipment .................................. Appendix A-6
Task 2133 Restrain a patient during flight .................................................................. Appendix A-7
Task 2137 Perform treatment to a patient .................................................................. Appendix A-7
APPENDIX B. QUICK FIX VOICE INTERCEPT OPERATOR TRAINING
B-1. EH-60 Mission Equipment Qualification ............................................................ Appendix B-1
B-2. Refresher Training ........................................................................................... Appendix B-1
B-3. Mission Training ............................................................................................. Appendix B-1
B-4. Continuation Training ...................................................................................... Appendix B-2
B-5. Task Contents .................................................................................................. Appendix B-2
Task 2151 Perform preflight inspection, power-up, shutdown, and
post-flight inspection on the AN/ALQ-151 (V) 2........................................ Appendix B-3
Task 2156 Key cryptographic systems ..................................................................... Appendix B-3
Task 2157 Perform initialization and BIT procedures ................................................. Appendix B-4
Task 2158 Program C-10026/USQ receiver control unit ............................................. Appendix B-5
Task 2159 Locate an emitter of interest using the AN/ALQ-151(V)2 ........................... Appendix B-5
Task 2160 Perform file management procedures ........................................................ Appendix B-5
Task 2161 Operate the countermeasures set, AN/TLQ-17A ........................................ Appendix B-6
Task 2163 Perform aircraft net mission ..................................................................... Appendix B-6
Task 2165 Operate the AN/ALQ-151(V) 2 under unusual conditions ........................... Appendix B-7
Task 2169 Perform mission planning requirements ..................................................... Appendix B-7
Task 2170 Perform INTEROP mission ..................................................................... Appendix B-8
GLOSSARY ......................................................................................................................Glossary-1
REFERENCES ...............................................................................................................References-1
INDEX ...................................................................................................................................Index-1
BLANK FORMS
êDA Form 5703-R (UH-60 Performance Planning Card)
TC 1-212
vi
PREFACE
The ATMs are basic documents that standardize aircrew training programs and flight evaluation
procedures. This manual provides specific guidelines for executing UH-60/EH-60 aircrew training. It is
based on the battle-focused training principles outlined in FM 25-101. It establishes crewmember qualification, refresher, mission, and continuation training and evaluation requirements. This manual applies
to all UH-60/EH-60 crew members and their commanders and standardization officers.
Used with TC 1-210, this manual will help aviation commanders at all levels develop a comprehensive
aircrew training program. By using the ATMs, commanders ensure that individual crew member and
aircrew proficiency is commensurate with their units' mission. They also ensure that aircrews routinely
employ standard techniques and procedures.
UH-60/EH-60 crew members will use this manual as a "how to" source for performing crew member
duties. It provides performance standards and evaluation guidelines so that crewmembers know the level
of performance expected and how that will be determined. Each task has a description that describes how
it should be done to meet the standard.
Standardization officers, evaluators/trainers, and unit trainers will use this manual, along with TC 1-210,
as a primary tool to assist the commander in implementing his aircrew training program. It provides the
minimum performance standards to which they must train and evaluate crewmembers.
If differences exist between the maneuver descriptions in TM 1-1520-237-10 and this manual, this
manual is the governing authority for training and flight evaluation purposes. Implementation of this
manual conforms to AR 95-1 and TC 1-210. If a conflict exists between this manual and TC 1-210,
TC 1-210 takes precedence.
The proponent of this publication is HQ TRADOC. Send comments and recommendations on DA Form
2028 through the aviation unit commander to Commander, US Army Aviation Center, ATTN: ATZQ-
ATB-ATM, Fort Rucker, AL 36362-5218.
This publication implements portions of STANAG 3114 (Edition Six)/Air Standard 60/16, Aeromedical
Training of Flight Personnel.
Unless this publication states otherwise, masculine nouns and pronouns do not refer exclusively to men.
This publication has been reviewed for operations security considerations.
TC 1-212
REFERENCES: Appropriate common references plus the following:
FAR/host-country regulations
FM 1-230
TM 1-1520-237-10
TASK 1003
Verify aircraft weight and balance.
CONDITIONS: Given mission cargo and passenger data and completed DD Forms 365-4
from the aircraft log book.
STANDARDS: Appropriate common standards plus verify that CG and gross weight
remain within limits for the duration of the flight per TM 1-1520-237-10.
DESCRIPTION: Using the completed DD Forms 365-4 from the aircraft logbook, ve rify
that aircraft gross weight and CG will remain within the allowable limits for the entire
flight. Note gross weight and/or loading restrictions/aircraft limitations. If there is no
completed DD Form 365-4 that meets mission requirements, refer to the unit weight and
balance technician or TM 55-1500-342-23.
REFERENCES:
AR 95-1
TM 1-1520-237-10
TM 55-1500-342-23
êTASK 1004
Prepare a performance planning card.
CONDITIONS: Given a blank DA Form 5703-R (UH-60 Performance Planning Card),
mission conditions, UH-60 engine torque factors, and aircraft basic weight.
NOTE 1: The charts in the AMCOM approved TM 1-1520-237-10, TM 1-1520-237-CL, TM
1-1520-253-10, and TM 1-1520-253-CL or the AMCOM approved performance planning
software must be used for performance planning.
NOTE 2: Tabular performance data usage and values are explained at the end of the task
DESCRIPTION.
STANDARDS: Appropriate common standards plus these additions/modifications:
1. Determine performance planning data necessary to complete the mission.
2. Determine when use of DA Form 5703-R is required.
6-19
3. Compute torque values ±2 percent.
TC 1-212
4. Compute gross weight values ±500 pounds.
5. Compute fuel flow ±100 pounds per hour.
6. Compute airspeeds ±5 KIAS.
7. Correctly determine maximum torque available, maximum allowable gross
weight (OGE), and GO/NO-GO (OGE) using tabular data found in the -CL.
DESCRIPTION:
1. Crew Duties. The PC will compute or direct other rated crew members to
compute the aircraft performance data required to complete the mission. He will verify the
computations and ensure aircraft performance meets mission requirements, and aircraft
limitations will not be exceeded.
2. Procedures.
a. Determine and have available aircraft performance data required to complete
the mission. DA Form 5703-R may be used as an aid to organize performance planning
data required for the mission. This form will be completed, in its entirety, for the following:
(1) RL progression training, annual ATP evaluations, and when required
during other training and evaluations.
(2) When the planned or actual aircraft gross weight for departure and/or
arrival is within 3,000 pounds of the maximum allowable gross weight OGE or when the
planned or actual gross weight is within 3,000 pounds of the maximum allowable gross
weight for cruise. To determine if the DA Form 5703-R must be completed, perform the
following procedures:
Step 1: DEPARTURE - Compare the maximum allowable gross weight for departure from
either the -CL tabular data or appropriate -10 HOVER chart with the planned or actual
aircraft gross weight.
Step 2: CRUISE – Compare the maximum allowable gross weight for cruise from the
appropriate -10 CRUISE chart with the planned or actual aircraft gross weight.
Step 3: ARRIVAL - Compare the maximum allowable gross weight for arrival from either
the -CL tabular data or appropriate -10 HOVER chart with the planned or actual aircraft
gross weight.
6-20
NOTE 1: If the dual-engine maximum torque available exceeds a torque limit, use the
tabular data equal to the torque limit, or enter the CRUISE chart at the torque limit line.
TC 1-212
NOTE 2: If the maximum torque available line used on a CRUISE chart is to the right of
the -10, Chapter 5 maximum gross weight limitation line, use the maximum gross weight
limit line.
b. When a significant change in the mission's conditions occurs, recompute all
affected values. A significant change is defined as any one of the following:
(1) An increase of over 10 degrees C, 2,000 feet PA, and/or 1,000 pounds
gross weight.
(2) An increase or decrease of an ETF by 0.03 or more.
NOTE: An increase or decrease of .03 ETF, normally caused by inaccurate information or a
change in aircraft, can significantly enhance or degrade single engine performance under
certain conditions. Therefore, when the ETF is different than the planned value, an update
of all affected values is required.
c. The data presented in the performance charts in the -10 are primarily
derived for either a "clean" or "high drag" aircraft. When the external equipment or
configuration differs significantly from the "clean" or "high drag" configuration, a drag
compensation will be made. This configuration is referred to as the "alternative or external
load" configuration and the appropriate drag compensation is described.
d. The procedures for determining performance planning data are the same for
the UH-60A/L, UH-60Q/HH-60L and EH-60A aircraft unless specifically noted in the
appropriate items.
e. DEPARTURE. (Figures 6-5 and 6-6 show the numerical sequence of each
task item for completing DA Form 5703-R (front and back).
(1) PA. Record forecast maximum pressure altitude for the mission and
pressure altitude for time of departure.
(2) FAT. Record forecast maximum free air temperature for the mission
and free air temperature for time of departure.
NOTE: Maximum pressure altitude and temperature will be used when computing all
items in the departure section except item 13. Item 13 will be computed using forecast
temperature and PA at time of departure.
6-21
(3) AIRCRAFT GWT. Record planned aircraft gross weight at takeoff.
This includes the aircraft basic weight, internal load, total fuel, and when applicable, ESSS
stores (exclude sling load).
TC 1-212
(4) FUEL WEIGHT. Record total planned fuel weight (internal and/or
external) at takeoff.
(5) STORES WEIGHT. Record the planned jettisonable weight of the
ESSS stores.
(6) SLING WEIGHT. Record the planned weight of the sling load.
(7) ATF/ETF. Record the ATF and ETFs in the appropriate blocks.
(8) TR. Use the aircraft TORQUE FACTOR chart to compute torque ratios
as described below.
Step 1: Enter the appropriate aircraft TORQUE FACTOR chart on the left at the
appropriate temperature. Move right to the ATF or ETF.
Step 2: Move straight down to the bottom of the chart, note the TORQUE RATIO ~ TR.
Record the TR.
(9) MAX TORQUE AVAILABLE. Use the appropriate MAXIMUM
TORQUE AVAILABLE chart to compute engine specification torque available as described
below.
NOTE 1: The maximum torque available is also referred to as INTERMEDIATE RATED
POWER (IRP) – 10 OR 30 MINUTE LIMIT.
NOTE 2: Certain temperature and pressure altitude combinations will exceed -10, Chapter
5 torque limitations. This item represents actual maximum torque available values.
During aircraft operations, -10, Chapter 5 torque limitations shall not be exceeded.
(a) T700-GE-700 engines.
Step 1: Enter the MAXIMUM TORQUE AVAILABLE chart at the appropriate
temperature then move right to the appropriate PRESSURE ALTITUDE ~ 1000 FT.
Step 2: Move down and read the SPECIFICATION TORQUE AVAILABLE PER ENGINE
~ %.
Step 3: If the ATF or ETF is less than 1.0, multiply the specification torque by the torque
ratio to obtain maximum torque available. An alternate method is to continue down
to the TORQUE RATIO, item 8. Move left to read the maximum TORQUE AVAILABLE ~
% per engine. Record MAX TORQUE AVAILABLE.
6-22
NOTE: Adjust maximum torque available as required for planned use of engine anti-ice
and/or cockpit heater according to the -10.
(b) T700-GE-701C engines.
TC 1-212
NOTE 1: The maximum torque available – 2.5 minute limit is also referred to as SINGLE-
ENGINE CONTINGENCY POWER – 2.5-MINUTE LIMIT.
Step 1: Enter the MAXIMUM TORQUE AVAILABLE – 10-MINUTE LIMIT chart for
dual-engine and 2.5-MINUTE LIMIT chart for single-engine at the appropriate FREE AIR
TEMPERATURE (FAT) ~ °C.
Step 2: Move right to the appropriate PRESSURE ALTITUDE ~ 1000 FT. line then move
down and read the TORQUE AVAILABLE PER ENGINE ~ %.
Step 3: If the ATF or ETF is less than 1.0, multiply the SPECIFICATION TORQUE by the
TORQUE RATIO to obtain maximum torque available.
Step 4: An alternate method is to enter the bottom of the TORQUE CONVERSION chart
at the TORQUE AVAILABLE PER ENGINE (SPECIFICATION TORQUE) ~ %. Move up
to the torque ratio, item 8, then left to read ACTUAL TORQUE AVAILABLE ~ %. Record
MAX TORQUE AVAILABLE.
NOTE 2: Adjust the maximum torque available as required for planned use of engine antiice and/or cockpit heater according to the -10.
(10) MAX ALLOWABLE GWT OGE / IGE. Use the appropriate HOVER
chart to compute maximum allowable gross weight for OGE/IGE as described below.
Annotate the computed maximum allowable gross weight OGE/IGE or the maximum gross
weight per -10, Chapter 5, whichever is less.
NOTE: If OGE capability does not exist, the MAX HOVER HEIGHT IGE, item 12, must be
computed.
(a) MAX ALLOWABLE GWT OGE / …
Step 1: Enter the HOVER chart at the TORQUE PER ENGINE ~ % (OGE) at the DUAL-
ENGINE MAX TORQUE AVAILABLE, item 9, then move right to the GROSS WEIGHT ~
1000 LB chart. If the dual-engine maximum torque available exceeds transmission torque
limits, use the DUAL ENGINE TRANS LIMIT line to compute the maximum allowable
gross weight OGE.
Step 2: Reenter the HOVER chart at the appropriate FREE AIR TEMP ~ °C and move
right to the appropriate PRESSURE ALTITUDE ~ 1000 FT, then move down to the GROSS
WEIGHT ~ 1000 LB chart. Read the maximum allowable gross weight OGE at the
intersection of this step and step 1 above. Record the MAX ALLOWABLE GWT OGE / ….
6-23
(b) MAX ALLOWABLE GWT … / IGE.
TC 1-212
Step 1: Enter the HOVER chart at the TORQUE PER ENGINE ~ % (IGE) at the DUAL-
ENGINE MAX TORQUE AVAILABLE, item 9, then move up to the desired IGE WHEEL
HEIGHT ~ FT (normally the 10-ft line), then move right to the GROSS WEIGHT ~ 1000 LB
chart. If the dual-engine maximum torque available exceeds transmission torque limits,
use the DUAL ENGINE TRANS LIMIT line to compute the maximum allowable gross
weight IGE.
Step 2: Reenter the HOVER chart at the appropriate FREE AIR TEMP. ~ °C and move
right to the appropriate PRESSURE ALTITUDE ~ 1000 FT then move down to the GROSS
WEIGHT ~ 1000 LB chart. Read the maximum allowable gross weight IGE at the
intersection of this step and step 1 above. Record the MAX ALLOWABLE GWT … / IGE.
(11) GO/NO-GO TORQUE OGE / IGE. Use the appropriate HOVER chart
as described below.
(a) OGE. Use maximum allowable gross weight OGE, item 10.
(b) IGE. Use maximum allowable gross weight IGE, item 10.
NOTE : GO/NO-GO is computed using the maximum forecast pressure altitude and
temperature for the mission. When the actual temperature is less than maximum, the
torque required to hover at a given gross weight is less. To ensure that structural limits
are not exceeded, or that OGE capabilities exist at maximum forecast temperature, reduce
GO/NO-GO by 1% for each 10 °C that actual temperature is less than maximum forecast
temperature.
Step 1: Enter the chart at the appropriate FREE AIR TEMP ~ °C.
Step 2: Move right to the appropriate PRESSURE ALTITUDE ~ 1000 FT.
Step 3: Move down to the weight(s) computed for item 10.
Step 4: Move left to the 10-foot hover line (or WHEEL HEIGHT ~ FT that will be used to
check the GO/NO-GO).
Step 5: Move down to read the GO/NO-GO torque value(s). Record the GO/NO-GO
TORQUE OGE / IGE.
(12) MAX HOVER HEIGHT IGE. If OGE capability does not exist, use the
appropriate HOVER chart to compute the MAX HOVER HEIGHT IGE, as described below.
Step 1: Enter the HOVER chart at the appropriate FREE AIR TEMP ~ °C and move right
to the appropriate PRESSURE ALTITUDE ~ 1000 FT, then move down to the take-off GW
~ 1000 LB, item 3 (plus sling load weight, item 6, if applicable), then move left to the
WHEEL HEIGHT ~ FT lines.
6-24
TC 1-212
Step 2: Reenter the bottom of the HOVER chart at the TORQUE PER ENGINE ~ % (IGE)
at the DUAL-ENGINE MAX TORQUE AVAILABLE, item 9, then up to the intersection from
step 1 above. Interpolate hover height as required. Record the MAX HOVER HEIGHT
IGE.
(13) PREDICTED HOVER TORQUE. Use the appropriate HOVER chart
as described below for torque required to hover. Use AIRCRAFT GWT, item 3, and current
PA, item 1, and FAT, item 2.
(a) Predicted hover torque (DUAL-ENGINE). Compute the torque
the same as for item 11 above using the AIRCRAFT GWT, item 3, instead of the MAX
ALLOWABLE GWT. Record DUAL-ENGINE PREDICTED HOVER TORQUE.
(b) Predicted hover torque (SINGLE-ENGINE). Double the
PREDICTED HOVER TORQUE value that was computed in step (a) above. If the value
exceeds the appropriate MAX TORQUE AVAILABLE, item 9, single-engine, record NA in
the appropriate block(s). Record SINGLE-ENGINE PREDICTED HOVER TORQUE.
(14) MIN SE - IAS - W/O STORES / W/STORES. Use the appropriate
CRUISE chart for the minimum single-engine airspeed with external stores and without
external stores as described below.
NOTE 1: If the aircraft will be operating without external stores, record NA in the w/stores
block.
NOTE 2: External stores are defined as a sling load, ESSS wing stores, or both.
Step 1: Enter the bottom of the CRUISE chart at one-half the SINGLE-ENGINE MAX
TORQUE AVALABLE, item 9, for the low ETF engine, but no more than one-half of the
TRANSMISSION TORQUE LIMIT.
Step 2: Move up to the first intersection of aircraft gross weight (without external stores).
Read left or right for the IAS ~ KTS. Record MIN SE – IAS – W/O STORES /….
NOTE 3: If aircraft will be operating with external stores, proceed with steps 3 and 4
below.
Step 3: Enter the bottom of the appropriate CRUISE chart at one-half the SINGLE-ENGINE
MAX TORQUE AVAILABLE, item 9, for the low ETF engine, but no more than one-half of
the TRANSMISSION TORQUE LIMIT.
Step 4: Move up to the first intersection of aircraft gross weight (with external stores).
Read left or right for the IAS ~ KTS. Record MIN SE – IAS – … / W/STORES.
6-25
TC 1-212
(15) ZERO FUEL WEIGHT: Use the appropriate HOVER chart from the
-CL to compute the adjusted ZERO FUEL WEIGHT as described below.
NOTE 1: The zero fuel weight on the DD Form 365-4 is computed using standard, average
or estimated weight for personnel, equipment and fuel. Actual weights may vary greatly
from those on the DD Form 365-4. It is also unrealistic to predict all possible
configurations that may be encountered on every mission. As a result, it may be necessary
to compute an adjusted ZERO FUEL WEIGHT. The method to determine adjusted ZERO
FUEL WEIGHT or to validate the DD Form 365-4 zero fuel weight is described below.
Step 1: Note free air temperature, pressure altitude, and total indicated fuel weight.
Step 2: While at a hover, note wheel height and hover torque.
Step 3: Enter the HOVER chart at the noted FREE AIR TEMP ~ °C. Move right to the
noted PRESSURE ALTITUDE ~ 1000 FT then down to the GROSS WEIGHT ~ 1000 LB
chart.
Step 4: Reenter the HOVER chart at the TORQUE PER ENGINE ~ % (IGE) at the noted
hover torque. Move up to the WHEEL HEIGHT ~ FT to the noted hover height then move
right to the intersection of step 3 above. Note aircraft gross weight.
Step 5: Subtract the noted total indicating fuel weight from the gross weight computed in
step 4 above. Record the adjusted ZERO FUEL WEIGHT.
NOTE 2: Although data needed to compute ZERO FUEL WEIGHT is noted at a hover, the
calculation may be made on the ground or, if not practical, shortly after takeoff or level off.
(16) REMARKS: Record appropriate mission information such as drag
factors, fuel requirements, and GO/NO-GO for sling loads.
NOTE: The GO/NO-GO TORQUE for sling loads is determined by using the same process
as item 11 above, using the MAX ALLOWABLE GWT OGE / … and a hover height that
suspends the load approximately 10 feet AGL.
f. CRUISE.
(1) PA. Record planned cruise pressure altitude.
(2) FAT. Record forecast temperature at the planned cruise pressure
altitude.
(3) TR. Use the TORQUE FACTOR chart to compute torque ratios, if
required. The torque ratio is computed the same as item 8, DEPARTURE data, using
cruise temperature instead of departure temperature.
6-26
TC 1-212
NOTE: The maximum torque available values found in the cruise charts of the -10 and the
tabular performance data of the -CL are adjusted for torque ratio.
(4) MAX TORQUE AVAILABLE. Compute maximum torque available for
dual- and single-engine the same as item 9, DEPARTURE data, using cruise temperature
and pressure altitude.
NOTE 1: Adjust as required for planned use of engine anti-ice and/or cockpit heater
according to the -10.
NOTE 2: Maximum torque available can be derived from the CRUISE chart by referencing
the TORQUE AVAILABLE ~ 30-MINUTE ATF 1.0 and/or 0.9 line, if shown. If the ATF or
ETF is between these values, interpolation is required. The maximum torque available –
30-minute limit for the T-700 engine and the 10-minute limit for the T-701C can also be
derived from the tabular data in the -CL. If the ATF is between 1.0 and 0.9, interpolation is
required.
(5) CT (critical torque). Record the value of one half the maximum torque
available of the engine with the lowest ETF.
NOTE: CT is the dual-engine torque value, which when exceeded, may not allow the
aircraft to maintain % RPM R within normal limits under single-engine operations in the
same flight conditions.
WARNING: During dual-engine flight, conditions that require torque settings greater
than the critical torque indicates the pilot is operating outside the aircraft low ETF singleengine capability. If operating dual-engine above the CT and an engine fails, malfunctions
or must be shut down; the pilot, in these circumstances, must immediately adjust torque,
airspeed and or gross weight to establish single-engine capability.
(6) MIN / MAX Vh – IAS (DUAL-ENGINE). Use the appropriate CRUISE
chart to compute the minimum/maximum Vh indicated airspeeds as described below.
(a) Clean and high drag configuration.
Step 1: Enter the bottom of the CRUISE chart at the MAX TORQUE AVAILABLE, item 4,
CRUISE data.
Step 2: Move up to the first intersection of AIRCRAFT GWT, item 3, DEPARTURE data.
Read left or right for minimum IAS ~ KTS. Record the DUAL-ENGINE MIN / … Vh – IAS.
If the maximum torque available line is right of the gross weight line, record 0 for the
MIN / … Vh - IAS.
Step 3: Continue up to the second intersection of AIRCRAFT GWT, item 3, DEPARTURE
data. Read left or right for maximum Vh IAS ~ KTS. Record the DUAL-ENGINE ... / MAX
Vh – IAS.
6-26.1
TC 1-212
NOTE: If the maximum torque available line is to the left of (does not intersect) the
AIRCRAFT GWT, item 3, DEPARTURE data, the aircraft cannot maintain dual-engine
level flight for the conditions. Item 18 must be computed and a new cruise altitude
selected.
(b) Alternative or external load configuration.
NOTE 1: For alternative or external load configurations, refer to the -10, Chapter 7,
Section VI, DRAG. Determine and add together the appropriate Drag Multiplying Factors.
NOTE 2: The torque change to compensate for drag (alternative or external load
configuration) at minimum Vh IAS is often negligible and not computed. The dual-engine
maximum Vh indicated airspeed is adjusted for alternate or external load configuration as
follows:
Step 1: Enter the CRUISE chart at maximum Vh IAS ~ KTS, (a) step 3 above, then left or
right to the curved dashed line then move up to read D TRQ ~ % FOR DRAG AREA OF 10
SQ FT of DF.
Step 2: Multiply the D TRQ times the drag multiplying factor. Subtract the result from
the maximum torque available used initially in (a) step 1 above.
Step 3: Reenter the bottom of the CRUISE chart at the adjusted torque value and move up
to the second intersection of AIRCRAFT GWT, item 3, DEPARTURE data. Read left or
right for maximum Vh IAS. Record the adjusted DUAL-ENGINE .../MAX Vh – IAS.
NOTE 3: If the adjusted maximum torque available line is to the left of (does not intersect)
the AIRCRAFT GWT, item 3, DEPARTURE data, the aircraft cannot maintain dual-engine
level flight for the conditions. Item 18 must be computed and a new cruise altitude
selected.
(7) CRUISE - IAS / TAS (DUAL-ENGINE). Record planned CRUISE – IAS /
… (inner IAS ~ KTS scale). Enter the CRUISE chart at cruise IAS and move laterally to
the outer TRUE AIRSPEED ~ KTS scale. Record DUAL-ENGINE CRUISE - … / TAS.
(8) CRUISE/CONTINUOUS TORQUE (DUAL-ENGINE). Use the
appropriate CRUISE chart to compute the torque required for cruise and continuous torque
available as described below.
NOTE: The continuous torque available is also referred to as MAXIMUM CONTINUOUS
POWER (MCP).
(a) Clean and high drag configuration.
Step 1: Enter the CRUISE chart at the selected cruise IAS in item 7 above. Move left or
right as appropriate to the aircraft GW ~ 1000 LB, item 3 (plus sling load weight, item 6, if
applicable), DEPARTURE data.
6-26.2
TC 1-212
Step 2: Move down to the TORQUE PER ENGINE ~ % line to read the CRUISE torque.
Record the DUAL-ENGINE CRUISE / … TORQUE.
Step 3: Renter the CRUISE chart at the selected cruise IAS in item 7 above. Move left or
right as appropriate to the TORQUE AVAILABLE - CONTINOUS line.
Step 4: Move straight down (do not follow the slant of the line) to the TORQUE PER
ENGINE ~ % to read the CONTINUOUS torque. Record the DUAL-ENGINE … /
CONTINUOUS TORQUE.
NOTE 1: If the selected CRUISE ~ IAS line is below the depicted TORQUE AVAILABLE –
CONTINOUS line, use the torque value indicated by the lowest extreme of the TORQUE
AVAILABLE ~ CONTINUOUS line.
NOTE 2: Adjust CRUISE / CONTINUOUS TORQUE for planned use of engine anti-ice
and/or heater.
(b) Alternative or external load configuration.
Step 1: Enter the appropriate CRUISE chart at the IAS in item 7 above, then move left or
right as appropriate to the curved dashed line. Move up to read the D TRQ ~ % FOR DRAG
AREA OF 10 SQ FT OF DF.
Step 2: Multiply the D TRQ ~ % by the drag multiplying factor.
Step 3: Add or subtract the value in step 2 to/from the uncorrected clean or high drag
cruise/continuous torque values in (a) steps 2 and 4 above (do not exceed the dual-engine
transmission torque limit). Record the adjusted CRUISE / CONTINUOUS TORQUE.
NOTE: If the adjusted torque value exceeds the dual-engine transmission torque limit, use
the dual-engine transmission torque limit and adjust cruise airspeed.
(9) CRUISE FUEL FLOW (DUAL-ENGINE).
(a) Cruise chart method. Use the appropriate CRUISE chart.
Step 1: Enter the bottom of the chart at the cruise torque value computed in item 8 above.
Step 2: Move up to TOTAL FUEL FLOW ~ 100 LB/HR and read cruise fuel flow. Record
the DUAL-ENGINE CRUISE FUEL FLOW.
NOTE: Adjust as required for planned use of engine anti-ice and cockpit heater according
to the -10.
6-26.3
(b) Engine fuel flow chart method. Use the SINGLE/DUAL-
ENGINE FUEL FLOW chart.
TC 1-212
Step 1: Enter the chart at the INDICATED TORQUE PER ENGINE ~ % for the cruise
torque value computed in item 8 above.
Step 2: Move right to the cruise PRESSURE ALTITUDE ~ 1000 FT.
Step 3: Move up to the DUAL-ENGINE FUEL FLOW ~ LB/HR line and read cruise fuel
flow. Record the DUAL ENGINE CRUISE FUEL FLOW.
NOTE: Adjust as required for FAT and/or planned use of engine anti-ice and cockpit
heater according to the -10.
(10) MAX END - IAS / TORQUE and MAX RANGE - IAS / TORQUE.
Use the appropriate CRUISE chart to compute maximum endurance indicated
airspeed/torque and maximum range indicated airspeed/torque as described below.
(a) Clean and high drag configuration.
Step 1: Enter the bottom of the appropriate CRUISE chart at AIRCRAFT GWT, item 3,
DEPARTURE data. Move up along the gross weight line to the intersection of the gross
weight line and the MAX END AND R/C line. Move left or right as required to the IAS ~
KTS value then read maximum endurance indicated airspeed. Record MAX END – IAS/….
Move down to the TORQUE PER ENGINE ~ % line, then read torque for the maximum
endurance indicated airspeed. Record MAX END - … / TORQUE.
Step 2: Continue up along the gross weight line to the intersection of the gross weight line
and the MAX RANGE line. Move left or right as required to the IAS ~ KTS value, then
read maximum range indicated airspeed. Record MAX RANGE – IAS / …. Move down to
the TORQUE PER ENGINE ~ % line, then read torque for the maximum range indicated
airspeed. Record MAX RANGE - … / TORQUE.
(b) Alternative or external load configuration.
NOTE 1: The torque change to compensate for drag (alternative or external load
configuration) at MAX END – IAS is often negligible and not computed.
NOTE 2: Maximum range airspeed is adjusted for alternative or external load
configurations as follows:
Step 1: Insert the indicated change in flat plate drag (DF ft2 ) into the formula found in the
-10, Chapter 7, Section IV, (6 Kts/10 ft2 XDF ft2 = N Kts) to derive the change in maximum
range IAS. See example in the -10, Chapter 7, Section IV.
6-26.4
Step 2: Subtract the IAS change in (b) step 1 above from (a) step 2 above. Record the
adjusted MAX RANGE – IAS / ….
TC 1-212
(11) MAX R/C - IAS / TORQUE. Use the MAX END – IAS, item 10 above,
and desired torque setting as described below.
Step 1: Use the MAX TORQUE AVAILABLE DUAL-ENGINE, item 4, CRUISE data. Record
this value for MAX R/C - … / TORQUE. Subtract the torque value found in MAX END - …
/ TORQUE, item 10 above from the MAX R/C - … / TORQUE to find the TORQUE
INCREASE – PER ENGINE - % TRQ.
Step 2: Use the CLIMB/DESCENT charts in the -10, Chapter 7, Section VII. Enter the
bottom of the CLIMB/DESCENT chart for clean or high drag, as appropriate, at the
TORQUE INCREASE – PER ENGINE - % TRQ using the value from Step 1 above.
Step 3: Move up to the GROSS WEIGHT ~ 1000 LB line from item 3 DEPARTURE data,
then move left to read the RATE OF CLIMB ~ FT/MIN.
Step 4: Use the AIRSPEED SYSTEM CORRECTIONS charts in the -10, Chapter 7,
Section IX. Enter the appropriate AIRSPEED SYSTEM CORRECTION chart for clean or
high drag at the MAX END – IAS / … from item 10 above. Move up to the appropriate
segmented line for the rate of climb value derived from Step 3 above (R/C GREATER OR
LESS THAN 1400 FT/MIN).
Step 5: Move left to read the CORRECTION TO ADD ~ KNOTS. Add or subtract this
value to/from the MAX END – IAS / … item 10. Record the resultant MAX R/C – IAS / ….
(12) MAX ALLOWABLE GWT and OPTIMUM IAS AT MAX
ALLOWABLE GWT (DUAL-ENGINE). Use the appropriate CRUISE chart to compute the
maximum allowable gross weight and optimum indicated airspeed at maximum allowable
gross weight as described below.
(a) Clean and high drag configuration.
Step 1: Enter the bottom of the CRUISE chart at the MAX TORQUE AVAILABLE, item 4,
CRUISE data.
Step 2: Move up to the intersection of MAXIMUM END AND R/C line then read the
indicating maximum gross weight. Record DUAL-ENGINE MAX ALLOWABLE GWT.
Read left or right for optimum indicated airspeed (IAS ~ KTS) at maximum allowable gross
weight. Record DUAL-ENGINE OPTIMUM IAS AT MAX ALLOWABLE GWT. If the
maximum torque available line is right of the gross weight lines, enter maximum gross
weight according to the -10, Chapter 5 limits then read left or right from the respective
value for optimum indicated airspeed at that maximum allowable gross weight.
6-26.5
(b) Alternative or external load configuration.
TC 1-212
NOTE: The dual-engine maximum allowable gross weight and optimum indicated airspeed
at maximum allowable gross weight are adjusted for alternate or external load
configuration as follows.
Step 1: Enter the CRUISE chart at the optimum indicated airspeed at maximum
allowable gross weight, (a) step 2 above, then read left or right to the curved dashed line.
Move up to read D TRQ ~ % FOR DRAG AREA OF 10 SQ FT of DF.
Step 2: Multiply the D TRQ times the drag multiplying factor. Subtract the result from
the maximum torque available value used initially in (a) step 1 above.
Step 3: Reenter the bottom of the CRUISE chart at the adjusted torque value then move
up to the intersection of MAX END AND R/C line. Read maximum gross weight and
optimum IAS at maximum allowable gross weight. Record the adjusted DUAL-ENGINE
MAX ALLOWABLE GWT and OPTIMUM IAS AT MAX ALLOWABLE GWT. If the
adjusted torque value is right of the gross weight lines, enter maximum gross weight
according to the -10, Chapter 5 limits then read left or right from the respective value for
optimum indicated airspeed at that maximum allowable gross weight.
(13) MIN / MAX Vh – IAS (SINGLE-ENGINE). Use the appropriate CRUISE
chart to compute the minimum/maximum Vh indicated airspeeds single-engine, as
described below.
(a) Clean and high drag configuration.
Step 1: Enter the bottom of the CRUISE chart at one-half the maximum torque available
for the low ETF engine, item 4 above, but no more than one-half of transmission torque
limit single-engine.
Step 2: Move up to the first intersection of the AIRCRAFT GWT, item 3, DEPARTURE
data then read left or right for minimum Vh IAS ~ KTS. Record the SINGLE-ENGINE MIN /
… Vh – IAS.
Step 3: Continue up to the second intersection of the AIRCRAFT GWT, item 3,
DEPARTURE data then read left or right for maximum Vh IAS. Record the SINGLE-
ENGINE … / MAX Vh – IAS.
NOTE: If the maximum torque available line is to the left of (does not intersect) the
AIRCRAFT GWT, item 3, DEPARTURE data, the aircraft cannot maintain single-engine
level flight for the conditions. Item 18 must be computed. As fuel is burned, single-engine
capability during the flight may be possible.
6-26.6
(b) Alternative or external load configuration.
TC 1-212
NOTE 1: The torque change to compensate for drag (alternative or external load
configuration) at minimum Vh IAS is often negligible and not computed.
NOTE 2: The maximum Vh indicated airspeed, single-engine, is adjusted for alternate or
external load configuration as follows:
Step 1: Enter the CRUISE chart at maximum Vh IAS ~ KTS, (a) step 3, above, then move
left or right to the curved dashed line. Move up to read D TRQ ~ % FOR DRAG AREA OF
10 SQ FT of DF.
Step 2: Multiply the D TRQ times the drag multiplying factor. Subtract the result from
the maximum torque available value used initially in (a) step 1 above.
Step 3: Reenter the bottom of the CRUISE chart at one-half the adjusted torque value and
move up to the second intersection of the AIRCRAFT GWT, item 3, DEPARTURE data.
Read left or right for maximum Vh IAS. Record the adjusted SINGLE-ENGINE .../MAX Vh –
IAS.
(14) CRUISE SPEED – IAS / TAS (SINGLE-ENGINE). Select an IAS that
falls within the range of MIN / MAX Vh – IAS, item 13 above. Convert to TAS as described
in item 7 above.
NOTE: Do not confuse single-engine cruise speed with emergency single-engine airspeed.
The emergency single-engine airspeed is the speed used immediately following an
emergency that requires adjustment to a single-engine airspeed. Single-engine cruise
speed and associated data is used in the pre-mission planning process. In the event an
engine fails, malfunctions or must be shut down, and single-engine operations are possible
but landing is not practical (such as over water, jungle, densely forested areas,
mountainous terrain or other impractical landing areas), the single-engine cruise speed
may be used after establishing emergency single-engine speed when required to reach the
intended landing area. The single-engine cruise speed may, in some instances, equal the
emergency single-engine speed.
(15) CRUISE/CONTINUOUS TORQUE (SINGLE-ENGINE). Use the
appropriate CRUISE chart to compute torque required for cruise and continuous torque
(single-engine), as described below.
(a) Clean and High Drag configuration.
Step 1: Enter the CRUISE chart at the selected single-engine cruise IAS, item 14 above.
Move left or right as appropriate to the aircraft GW ~ 1000 LB, item 3, DEPARTURE data.
6-26.7
Step 2: Move down to the TORQUE PER ENGINE ~ % line to read the CRUISE torque,
then double the torque value. Record the SINGLE-ENGINE CRUISE/… TORQUE.
TC 1-212
Step 3: Reenter the CRUISE chart at the selected CRUISE – IAS in item 14 above. Move
left or right as appropriate to the TORQUE AVAILABLE - CONTINOUS line.
Step 4: Move straight down (do not follow the slant of the line) to the TORQUE PER
ENGINE ~ % to read the CONTINUOUS torque. Record the SINGLE-ENGINE
…/CONTINUOUS TORQUE. .
NOTE 1: If the selected CRUISE ~ IAS line is below the depicted TORQUE AVAILABLE –
CONTINOUS line, use the torque value indicated by the lowest extreme of the TORQUE
AVAILABLE ~ CONTINUOUS line.
NOTE 2: Adjust CRUISE / CONTINUOUS TORQUE for planned use of engine anti-ice
and/or heater.
(b) Alternative or external load configuration.
Step 1: Enter the appropriate CRUISE chart at the selected single-engine cruise IAS in
item 14 above the move left or right to the curved dashed line. Move up to read the D TRQ
~ % FOR DRAG AREA OF 10 SQ FT OF DF.
Step 2: Multiply the D TRQ ~ % by the drag multiplying factor.
Step 3: Add or subtract the value in step 2 to/from the uncorrected clean or high drag
cruise/continuous torque values in (a) steps 2 and 4 above, then double the torque value (do
not exceed the single-engine transmission torque limit). Record the adjusted SINGLE-
ENGINE CRUISE / CONTINUOUS TORQUE.
NOTE: If the adjusted torque value exceeds the single-engine transmission torque limit,
use the single-engine transmission torque limit and adjust cruise airspeed.
(16) CRUISE FUEL FLOW (SINGLE-ENGINE).
(a) Cruise chart method. Use the appropriate CRUISE chart.
Step 1: Enter the bottom of the chart at the torque value computed in item 15 above.
Step 2: Move up to TOTAL FUEL FLOW ~ 100 LB/HR and read the cruise fuel flow.
Divide the cruise fuel flow value in half. Record the SINGLE-ENGINE CRUISE FUEL
FLOW.
NOTE: Adjust as required for planned use of engine anti-ice and cockpit heater according
to the -10.
6-26.8
(b) Engine fuel flow chart method. Use the SINGLE/DUAL-
ENGINE FUEL FLOW chart.
Step 1: Enter the chart at the INDICATED TORQUE PER ENGINE ~ % for the cruise
torque value computed in item 15 above.
TC 1-212
Step 2: Move right to the cruise PRESSURE ALTITUDE ~ 1000 FT.
Step 3: Move down to the SINGLE-ENGINE FUEL FLOW ~ LB/HR line and read fuel
flow value. Record the SINGLE-ENGINE CRUISE FUEL FLOW.
NOTE: Adjust as required for FAT and/or planned use of engine anti-ice and cockpit
heater according to the -10.
(17) MAX ALLOWABLE GWT and OPTIMUM IAS AT M AX
ALLOWABLE GWT (SINGLE-ENGINE). Use the appropriate CRUISE chart to compute
the maximum allowable gross weight, and optimum indicated airspeed at maximum
allowable gross weight, single-engine, as described below.
(a) Clean and high drag configuration.
Step 1: Enter the bottom of the CRUISE chart at one-half the SINGLE-ENGINE MAX
TORQUE AVAILABLE, item 4, CRUISE data, for the low ETF engine, but no more than
one-half of transmission torque limit single-engine.
Step 2: Move up to the intersection of MAX END AND R/C line then read the indicating
maximum allowable gross weight. Record the SINGLE-ENGINE MAX ALLOWABLE GWT.
Read left or right for optimum IAS ~ KTS at maximum allowable gross weight. Record the
SINGLE-ENGINE OPTIMUM IAS AT MAX ALLOWABLE GWT.
NOTE: If the torque used does not intersect aircraft gross weight, the aircraft cannot
maintain single-engine level flight for the conditions. Item 18 must be computed. As fuel is
burned, single-engine capability during the flight may be possible.
(b) Alternative or external load configuration.
NOTE 1: The single-engine maximum allowable gross weight and optimum indicated
airspeed at maximum allowable gross weight are adjusted for alternate or external load
configuration as follows:
Step 1: Enter the CRUISE chart at the optimum indicated airspeed at maximum
allowable GWT, step 2 above. Read left or right to the curved dashed line then move up to
read D TRQ ~ % FOR DRAG AREA OF 10 SQ FT of DF.
6-26.9
Step 2: Multiply the D TRQ times the drag multiplying factor. Subtract the result from
the maximum torque available value used initially in (a) step 1 above.
TC 1-212
Step 3: Reenter the bottom of the CRUISE chart at one-half the adjusted torque value
then move up to the intersection of MAX END AND R/C line. Read maximum allowable
gross weight and optimum IAS at maximum allowable gross weight. Record the adjusted
SINGLE-ENGINE MAX ALLOWABLE GWT and OPTIMUM IAS AT MAX ALLOWABLE
GWT.
NOTE 2: If the adjusted torque value does not intersect the AIRCRAFT GWT, item 3,
DEPARTURE data, the aircraft cannot maintain single-engine level flight for the
conditions. Item 18 must be computed. As fuel is burned, single-engine capability during
the flight may be possible.
(18) MAX ALTITUDE – MSL. When cruise flight, dual and/or singleengine, is not possible at the planned cruise pressure altitude, item 1, CRUISE data, use
the appropriate CRUISE chart to compute the maximum altitude MSL as described below.
NOTE: Several different cruise charts may be referenced when selecting an optimum
maximum cruise altitude, using a variety of temperature, altitude, aircraft gross weight
and cruise IAS combinations.
(a) Dual-engine.
Step 1: Enter the appropriate cruise chart at the maximum torque available for that chart.
Move up to the second intersection of the aircraft gross weight, item 3, DEPARTURE data.
Step 2: Move left or right to read the IAS ~ KTS. If the indicated IAS ~ KTS is less than
the planned cruise IAS, adjust planned temperature, altitude, IAS and/or gross weight
combinations to find a suitable cruise altitude. Record the DUAL-ENGINE MAX
ALTITUDE – MSL.
(b) Single-engine.
NOTE 1: When the capability to maintain level flight after an engine failure or
malfunction is not possible, continued flight may be possible by descending to a lower
pressure altitude. Adjust to the appropriate maximum endurance indicated airspeed and
adjust collective to the maximum torque available to attain minimum rate of descent as
required.
Step 1: Enter the appropriate CRUISE chart at one half of the SINGLE-ENGINE MAX
TORQUE AVAILABLE, item 4, CRUISE data, of the lowest ETF engine.
6-26.10
TC 1-212
Step 2: Move up until intersecting the MAX END AND R/C line and interpolate the
maximum gross weight. If the interpolated maximum gross weight is less than the aircraft
gross weight, item 3, DEPARTURE data, progressively use lower altitude/temperature
combination CRUISE charts until interpolated gross weight is at or greater than the
aircraft gross weight. Record the SINGLE-ENGINE MAX ALTITUDE – MSL.
WARNING: If allowable altitude/temperature combination cruise charts do not yield a
gross weight greater than/or equal to the AIRCRAFT GWT, item 3, DEPARTURE data,
level flight is not possible. Record NA in item 18.
NOTE 2: Changes in maximum torque available due to changes in pressure altitude and
temperature may be derived from the -CL tabular performance data.
(19) EMERGENCY SE – IAS. This value is the emergency single-engine
airspeed based on the mission and briefed to the crew for the purpose of crew coordination.
This airspeed is selected from the MIN / MAX Vh - IAS range computed in item 13,
CRUISE data and is used immediately following an emergency that requires adjustment to
a single-engine airspeed. When an aircraft does not have single-engine capability, the MAX
END - IAS, item 10, or the OPTIMUM IAS AT MAX ALLOWABLE GWT, item 17, as
appropriate, should be briefed as the emergency single-engine airspeed.
NOTE 1: Normally only one EMERGENCY SE – IAS is selected. However, when the MIN
/ MAX Vh – IAS range, item 13, is wide, the crew may select two emergency single engine
airspeeds, one slow and one fast based on mission profile, modes of flight, environmental
conditions or other factors.
NOTE 2: There is no power margin available when operating single-engine at the MIN /
MAX Vh - IAS, item 13. These airspeeds are computed using the maximum torque
available single-engine for the lowest ETF engine. It is not recommended that the aircraft
be flown at airspeeds that require maximum power for continued single-engine flight.
(20) MAX ANGLE. Use the AIRSPEED FOR ONSET OF BLADE STALL
chart in the -10, Chapter 5, to compute the maximum bank angle for the planned cruise IAS
as described below.
Step 1: Enter the chart at the cruise PRESSURE ALTITUDE ~ 1000 FT. Move right to
the cruise temperature FAT °C.
Step 2: Move down to the aircraft GROSS WEIGHT ~ 1000 LBS, item 3 (plus sling load
weight, item 6, if applicable), DEPARTURE data then move left to the ANGLE OF BANK ~
DEG chart.
6-26.11
TC 1-212
Step 3: Reenter the chart at the INDICATED AIRSPEED ~ KTS at the planned cruise
airspeed, item 7 above, then move up to the ANGLE OF BANK ~ DEG chart. Record
derived MAX ANGLE or 60° whichever is less.
(21) Vne - IAS. Use the appropriate AIRSPEED OPERATING
LIMITATIONS chart of the -10, Chapter 5, to compute the velocity not to exceed as
described below.
Step 1: Enter the chart at the cruise FREE AIR TEMPERATURE ~ °C. Move right to the
cruise PRESSURE ALTITUDE ~ FT.
Step 2: Move down to the aircraft GROSS WEIGHT ~ LBS, item 3 (plus sling load weight,
item 6, if applicable), DEPARTURE data. If the COMPRESSIBILITY LIMITS ~ FAT or the
MACH LIMIT dashed temperature line (-10 to -50 °C) is reached prior to the aircraft
GROSS WEIGHT ~ LBS, stop there.
Step 3: Move left to the MAXIMUM INDICATED AIRSPEED (VNE) ~ KNOTS line for the
Vne value. Record Vne-IAS.
g. ARRIVAL. Complete this section if arrival conditions at destination differ
significantly from departure conditions as defined in paragraph 2b above.
(1) PA. Record forecast pressure altitude for time of arrival. If unavailable,
use maximum forecast pressure altitude for the mission.
(2) FAT. Record forecast temperature for time of arrival. If unavailable,
use maximum forecast temperature for the mission.
(3) LANDING GWT. Record the estimated gross weight for arrival.
(4) TR. Compute the torque ratios for dual- and single-engine the same as
item e(8), DEPARTURE data, using arrival temperature and pressure altitude.
(5) MAX TORQUE AVAILABLE. Compute maximum torque available for
dual- and single-engine the same as item e(9), DEPARTURE data, using arrival forecast
pressure altitude and temperature.
NOTE 1: Adjust as required for planned use of engine anti-ice and/or cockpit heater
according to the -10.
NOTE 2: This information can also be derived from the tabular performance data in the
-CL.
(6) PREDICTED HOVER TORQUE. Compute the predicted hover torque
the same as item e(13), DEPARTURE data, using arrival forecast pressure altitude and
temperature.
6-26.12
TC 1-212
(7) MAX ALLOWABLE GWT OGE/IGE. Compute the maximum
allowable gross weight the same as item e(10), DEPARTURE data, using arrival forecast
pressure altitude and temperature.
(8) MAX HOVER HEIGHT IGE. If OGE capability does not exist, compute
the maximum hover height IGE the same as item e(12), DEPARTURE data, using arrival
forecast pressure altitude and temperature.
(9) MIN SE – IAS - W/O STORES / W/STORES. Compute the minimum
single-engine airspeed with external stores and without external stores the same as item
e(14), DEPARTURE data, using arrival forecast pressure altitude and temperature.
h. Updates. The PPC may be updated in flight or on the ground as the mission
progresses. Updates are required when there is an intent to land and/or takeoff and when
operating within 3,000 pounds of the MAX ALLOWABLE GWT (OGE), there is an increase
of 500-feet pressure altitude, and/or 5 °C from the planned PPC.
(1) AIRCRAFT WEIGHT. Update the aircraft weight as described below.
(a) When internal and/or external load weights have not
changed. Add the total remaining indicated fuel weight (internal/external) to the zero fuel
weight computed, item 15, DEPARTURE data.
(b) When internal and/or external load weights have changed.
Perform a hover check to determine a readjusted zero fuel weight as described in item e(15),
DEPARTURE data.
NOTE: The tabular performance data in the back of the -CL will be used for the following
computations.
(2) MAX TORQUE AVAILABLE. Use the appropriate tabular
performance data MAXIMUM TORQUE AVAILABLE table as described in Figure 6-3.
Step 1: Enter the table at the appropriate HP~FT (pressure altitude) and move right to
the ATF 1.0 or 0.9 value as required.
Step 2: Continue right to the appropriate FREE AIR TEMPERATURE ~ °C column. Read
MAX TORQUE AVAILABLE.
NOTE 1: See tabular performance data examples in Figure 6-3.
NOTE 2: The ATFs shown on the chart are 1.0 and 0.9. If the aircraft has an ATF
between these values, interpolation is required.
6-26.13
(3) MAX ALLOWABLE GWT OGE. Use the APPROPRIATE MAXIMUM
OGE HOVER WEIGHT AND TORQUE REQUIRED table as described below.
TC 1-212
Step 1: Enter the table at the appropriate HP ~ FT (pressure altitude) and move right to
the GW ~ 100 LB line.
Step 2: Continue right to the appropriate FREE AIR TEMPERATURE ~ °C column.
Multiply the indicated value by 100 to determine the MAX ALLOWABLE GWT OGE.
Step 3: Move down to Q ~ OGE ~ % line. Read torque required to hover OGE, at the MAX
ALLOWABLE GWT OGE.
NOTE : See tabular performance data examples in Figure 6-4.
(4) GO/NO-GO OGE. Use the appropriate MAXIMUM OGE HOVER
WEIGHT AND TORQUE REQUIRED table as described below.
Step 1: Enter the table at the appropriate HP ~ FT (pressure altitude) and move right to
the Q ~ IGE ~ % line.
Step 2: Continue right to the appropriate FREE AIR TEMPERATURE ~ °C column. Read
the GO/NO-GO OGE torque value. This is also the torque required to hover IGE, at the
MAX ALLOWABLE GWT OGE.
NOTE: See tabular performance data examples in Figure 6-4.
i. Tabular Performance Data. The following examples are provided to
explain the tabular performance data presented in the -CL.
6-26.14
TC 1-212
MAXIMUM TORQUE AVAILABLE* - 30 MINUTE LIMIT
ANTI-ICE OFF T700-GE-700 ENGINE (CONTINUED)
HP
FREE AIR TEMPERATURE ~ °C
~FT ATF -15 -10 -5 0 5 10 15
8000 1.0 89 90 90 90 88 85 84
0.9 89 88 86 85 83 81 78
Pressure Altitude (PA)
ATF – If the aircraft ATF is between 0.9 and
1.0, Interpolate the maximum torque
available as described below.
Free air temperature (FAT)
EXAMPLE: UH-60A/Q
PA: +8000’
ATF: 0.96
FAT: +10°C
96 is 6/10 of the difference between ATF .90 (0.9) and 1.00 (1.0)
Maximum Torque Available
85 – 81 = 4 % TRQ
4 X 6/10 = 2.4 % TRQ
81 + 2.4 = 83.4 % maximum torque available
Figure 6-3. Maximum torque available chart.
6-26.15
TC 1-212
MAXIMUM OGE HOVER WEIGHT AND TORQUE REQUIRED
ANTI-ICE OFF T700-GE-700 ENGINE (CONTINUED)
HP FREE AIR TEMPERATURE ~°C
~FT 10 15 20 25
ATF
* 1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9
GW ~ 100 LB 173 166 169 162 166 157 162 152
8000 Q ~ OGE ~ % 85 81 84 78 82 75 79 72
Q ~ IGE ~ % 73 69 71 67 70 64 67 62
GW ~ 100 LB (aircraft gross weight) – Multiply this
value times 100.
Q ~ OGE ~ % (torque required to hover OGE at 100-
feet wheel height) at maximum allowable gross weight
OGE above (GW ~100 LB).
Q ~ IGE ~ % (torque required to hover IGE at 10-feet
wheel height) at maximum allowable gross weight OGE
above (GW ~100 LB).
EXAMPLE: UH-60A/Q
PA: +8000’
ATF: 0.96
FAT: +10°C
.96 is 6/10 of the difference between ATF .90 (0.9) and 1.00 (1.0)
GW~100 LB
Maximum allowable gross weight OGE, (0.9): 166 X 100 = 16,600, (1.0): 173 X 100 = 17,300 pounds.
17,300 – 16,600 = 700 pounds
700 X 6/10 = 420 pounds
16600 + 420 = 17,020 pounds maximum allowable gross weight OGE
Q~OGE~%
85 – 81 = 4 % TRQ
4 X 6/10 = 2.4 % TRQ
81 + 2.4 = 83.4 % TRQ required to hover 17,020 pounds OGE
Q~IGE~%
73 – 69 = 4 % TRQ
4 X 6/10 = 2.4 %, TRQ
69 + 2.4 = 71.4 % TRQ required to hover 17,020 pounds IGE
71.4% TRQ is also the GO/NO-GO OGE
Figure 6-4. Maximum OGE hover weight and torque required chart.
6-26.16
TC 1-212
UH-60 PERFORMANCE PLANNING CARD
For use of this form, see TC 1-212: The proponent agency is TRADOC.
DEPARTURE
AIRCRAFT GWT: (3) lbs PA: (1) / (1) FAT: (2) °C / (2) °C
FUEL WEIGHT: (4) lbs
STORES WEIGHT: (5) lbs
DUAL-ENGINE SINGLE-ENGINE
#1 #2
SLING WEIGHT: (6) lbs ATF: (7) ETF: (7) ETF: (7)
ZERO FUEL WEIGHT: (15) lbs TR: (8) TR: (8) TR: (8)
MAX TORQUE AVAILABLE (9) % (9) % (9) %
MAX ALLOWABLE GWT OGE / IGE (10) / (10)
GO/NO-GO TORQUE OGE / IGE (11) % / (11) %
MAX HOVER HEIGHT IGE (12) ft
PREDICTED HOVER TORQUE (13) % (13) % (13) %
MIN SE-IAS - W/O STORES / W/STORES (14) kts / (14) kts
REMARKS: (16)
CRUISE
PA: (1) ft FAT: (2) °C MAX ANGLE: (20) ° Vne-IAS: (21) kts
DUAL-ENGINE SINGLE-ENGINE
#1 #2
TR: (3) TR: (3) TR: (3)
MAX TORQUE AVAILABLE CT (5) % (4) % (4) % (4) %
MIN / MAX Vh - IAS (6) kts/ (6) kts (13) kts / (13) kts
CRUISE - IAS / TAS (7) / (7) (14) kts/ (14) kts
CRUISE / CONTINUOUS TORQUE (8) %/ (8) % (15) %/ (15) %
CRUISE FUEL FLOW (9) pph (16) pph
MAX END - IAS / TORQUE (10) kts/ (10) %
MAX RANGE - IAS / TORQUE (10) kts/ (10) %
MAX R/C - IAS / TORQUE (11) kts/ (11) %
MAX ALLOWABLE GWT (12) lbs (17) lbs
OPTIMUM IAS AT MAX ALLOWABLE GWT (12) kts (17) kts
MAX ALTITUDE - MSL (18) ft (18) ft
EMERGENCY SE - IAS (19) kts
DA FORM 5703-R
Figure 6-5. Sample UH-60 Performance Planning Card (front).
6-26.17
TC 1-212
ARRIVAL
LANDING GWT: (3) lbs PA: (1) ft FAT: (2) °C
DUAL-ENGINE SINGLE-ENGINE
#1 #2
TR: (4) TR: (4) TR: (4)
MAX TORQUE AVAILABLE (5) % (5) % (5) %
PREDICTED HOVER TORQUE (6) % (6) % (6) %
MAX ALLOWABLE GWT OGE / IGE (7) / (7)
MAX HOVER HEIGHT IGE (8) ft
MIN SE-IAS - W/O STORES / W/STORES (9) kts / (9) kts
REMARKS:
PAGE 2, DA FORM 5703-R
Figure 6-6. Sample UH-60 Performance Planning Card (back).
6-26.18
TC 1-212
Glossary-1
GLOSSARY
ACE analysis control element
ACFT aircraft
ACP air control point
ADF automatic direction finder
AFCS automatic flight control system
AGL above ground level
AH attack helicopter
AHO above highest obstacle
AIM Aeronautical Information Manual
ALSE aviation life support equipment
ALTR alternate
AMC air mission commander
êAMCOM Aviation and Missile Command (U.S. Army)
ANVIS aviator's night vision imaging system
APART annual proficiency and readiness test
APU auxiliary power unit
AR Army regulation
ARNG Army National Guard
ARTEP Army training and evaluation program
ASE aircraft survivability equipment
ASET aircrew survivability equipment trainer
TC 1-212
Glossary-2
ASR airport surveillance radar
ATC air traffic control
ATF aircraft torque factor
ATIS automatic terminal information service
ATM aircrew training manual
ATP aircrew training program
ATTN attention
AZ Arizona
BDHI bearing-distance-heading indicator
BII basic issue items
BITE built-in test equipment
êC Celsius
C&E communication/electronics
CDU central display unit
CE crew chief (maintenance personnel)
CG center of gravity
CIS command instrument system
CL checklist
COMPT compartment
CONT continuous
CONUS continental United States
CP communications process; control point
CPCI communications processor control indicator
CPU central processing
TC 1-212
Glossary-3
CTR crew training record
DA Department of the Army
DAC Department of the Army civilian
DD Department of Defense (applies to form)
DEC digital electronic control
DECU digital electronic control unit
D/F direction finder
DF direction finding
DFCU direction finding control unit
êDEG degree
DH decision height
DIR direct
DMF drag multiplying factor
DOD Department of Defense
EA electronic attack
ECCM electronic counter-countermeasures
ECU electrical control unit
EH electronic helicopter
EMER emergency
EMS emergency medical service
END endurance
ENG engine
ERFS extended range fuel system
TC 1-212
Glossary-4
ESSS external store support system
ETA estimated time of arrival
ETE estimated time en route
ETF engine torque factor
ETL effective translational lift
ETP exportable training packet
F Fahrenheit
FAA Federal Aviation Administration
FAC flight activity category
FAR Federal Aviation regulation
FAT free air temperature
FI nonrated crew member instructor
FIH Flight Information Handbook
FLIP flight information publication
FM field manual; frequency modulated
FPM feet per minute
FPS flight path stabilization
FS flight simulator
ft feet
FW fixed wing
GEN generator
GPS global positioning system
GR grade
GWT gross weight
TC 1-212
Glossary-5
HDG heading
Hg mercury
HIRSS Hover Infrared Suppressor System
HIT health indicator test
HQ headquarters
hr hour
HSI horizontal situation indicator
HUD heads-up display
I instructor
IAS indicated airspeed
IATF individual aircrew training folder
ICAO International Civil Aviation Organization
ICS intercommunication system
ID identification
IE instrument examiner
IFF identification, friend or foe (radar)
IFR instrument flight rules
IGE in-ground effect
IINS integrated inertial navigation system
ILS instrument landing system
IMC instrument meteorological conditions
IOP interoperability
IP instructor pilot
TC 1-212
Glossary-6
IR infrared
êIRP intermediate rated power
IV intravenous
KIAS knots indicated airspeed
kt knot
KTAS knots true airspeed
KTS knots
LOB lines-of-bearing
LOC localizer
LS left seat
LSE landing signalman enlisted
LZ landing zone
MAP missed approach point
max maximum
êMCP maximum continuous power
MCS master control station
ME maintenance test flight evaluator
MEDEVAC medical evacuation
METL mission essential task list
METT-T mission, enemy, terrain, troops, and time available
MIJI meaconing, intrusion, jamming, and interference
min minimum
MO flight medic or other medical personnel
MOPP mission-oriented protective posture
TC 1-212
Glossary-7
MOS military occupational specialty
MOU memorandum of understanding
MP maintenance test pilot
êMSL mean sea level
MTF maintenance test flight
N night
NA not applicable; ungraded (for grade slip purposes)
NAS National Airspace System
NATO North Atlantic Treaty Organization
NAV navigation
NAVAID navigational aid
NBC nuclear, biological, chemical
NCM nonrated crew member
NDB nondirectional beacon
Ng engine gas generator speed
NGR National Guard regulation
no number
NOE nap of the earth
NORM normal
NOTAM notice to airmen
Np engine power turbine speed
NVD night vision device
NVG night vision goggles
NVS night vision system
TC 1-212
Glossary-8
OGE out-of-ground effect
P pilot not on the controls
P* pilot on the controls
PA pressure altitude
pam pamphlet
PAR precision approach radar
PC pilot in command
PCL power control lever
PDU pilot's display unit
PI pilot
PMS preventive maintenance service
PNVS pilot night vision system
POI program(s) of instruction
POS position
PPC performance planning card
psi pounds per square inch
PTT push to talk
pub publication
PZ pickup zone
R reproducible
R/C rate of climb
RCM rated crew member
RCU receiver control unit
REL release
TC 1-212
Glossary-9
RF radio frequency
RFI radio frequency interference
RL readiness level
ROM read only memory
ROS remote out station
ROZ restricted operating zone
RPM revolutions per minute
RPM R revolutions per minute rotor
RS right seat
RW rotary wing
SALUTE size, activity, location, unit, time, equipment
SAS stability augmentation system
SAT systems approach to training
SDU signal display unit
êSE single-engine
SEL select; selection
SFTS synthetic flight training systems
SI nonrated crew member standardization instructor
SIF selective identification feature
SINCGARS single-channel ground and air radio system
SKED (company trade name for litter)
SM statute mile
SM-TG soldier's manual-trainer's guide
SOI signal operation instructions
TC 1-212
Glossary-10
SOP standing operating procedure
SP standardization instructor pilot
sq square
SSN social security number
STAB stabilator
STABO a system for extracting personnel by helicopter (the
combined first letters of the surnames of the five persons
who designed the system)
STANAG standardization agreement
std standard
STP soldier training publication
sys system
TADS target acquisition and designation system
TAS true airspeed
TB technical bulletin
TC training circular
TGT turbine gas temperature
TM technical manual
TR torque ratio
TRADOC United States Army Training and Doctrine Command
êTRQ torque
UH utility helicopter
UH-60FS UH-60 flight simulator
UHF ultra high frequency
US United States (of America)
USAAVNC United States Army Aviation Center
TC 1-212
Glossary-11
USAF United States Air Force
USAR United States Army Reserve
USARI United States Army Research Institute
UT unit trainer
VFR visual flight rules
Vh maximum speed in level flight with maximum power
VHF very high frequency
VMC visual meteorological conditions
Vne velocity never exceed (airspeed limit)
VOR VHF omnidirectional range
VSI vertical speed indicator
WB wideband
WX weather
XFD cross-feed
Z/Zulu coordinated universal time (UTC)
TC 1-212
References-1
REFERENCES
SOURCES USED
These are the sources quoted or paraphrased in this publication.
Army Regulations
AR 95-10. The US Military Notice to Airmen (NOTAM) System. 17 November 1990.
AR 385-95. Army Aviation Accident Prevention. 20 May 1991.
AR 611-101. Commissioned Officer Classification System. 1 July 1994.
Department of the Army Pamphlet
DA Pamphlet 351-4. Army Formal Schools Catalog. 30 October 1993.
Department of the Navy Manual
Shipboard Aviation Facilities Resume.
Department of Defense Airman's Information Manual
DOD AIM 86-100. Operation and Maintenance Overview General Triservice Mode 4
Handbook. May 1987.
This publication is available from Commanding Officer, ATTN: Code 2111, Naval Electronic
Systems Engineering Activity, St. Inigoes, MD 20684-0010, or WR-ALC/MMAM-AIMS,
ATTN: DOD AIMSPO, Robins AFB, GA 31098-5609.
Joint Chiefs of Staff Publication (JCS Pub)
Joint Pub 3-04.1. Joint Tactics, Techniques, and Procedures for Shipboard Helicopter
Operations. 28 June 1993.
Field Manuals
FM 1-101. Aviation Battlefield Survivability. 5 December 1990.
FM 1-103. Airspace Management and Army Air Traffic in a Combat Zone. 30 December 1981.
FM 1-104. Tactics, Techniques, and Procedures for Forward Arming and Refueling Points. 12
September 1994.
FM 1-107. Air-to-Air Combat. 12 October 1984.
FM 1-202. Environmental Flight. 23 February 1983.
FM 1-230. Meteorology for Army Aviators. 30 September 1982.
FM 1-300. Flight Operations Procedures. 22 June 1993.
TC 1-212
References-2
FM 1-302. Aviation Life Support Equipment (ALSE) for Army Aircrews. 30 September 1983.
FM 1-500. Army Aviation Maintenance. 27 January 1995.
FM 3-3. Chemical and Biological Contamination Avoidance. 16 November 1992.
FM 3-3-1. Nuclear Contamination Avoidance. 9 September 1994.
FM 3-100. NBC Defense, Chemical Warfare, Smoke, and Flame Operations. 23 May 1991.
FM 8-10-6. Medical Evacuation in a Theater of Operations: Tactics, Techniques, and
Procedures. 31 October 1991.
FM 8-14. Fundamentals of Respiratory Therapy. 1 February 1979.
FM 8-15. Medical Support in Divisions, Separate Brigades, and the Armored Cavalry Regiment.
21 September 1972.
FM 8-230. Medical Specialist. 24 August 1984.
FM 8-273-1. Nursing Skills for Allied Health Services (Vols 1 and 2). March 1982.
FM 8-273-2. Nursing Skills for Allied Health Services (Vol 3). March 1982.
FM 10-68 . Aircraft Refueling. 29 May 1987.
FM 17-95. Cavalry Operations. 19 September 1991.
FM 21-26. Map Reading and Land Navigation. 7 May 1993.
FM-21-60. Visual Signals. 30 September 1987.
FM 24-1. Signal Support in the AirLand Battle. 15 October 1990.
FM 24-35. (O) Signal Operation Instructions "The SOI" (U). 26 October 1990.
FM 24-35-1. Signal Supplemental Instructions. 2 October 1990.
FM 31-19. Military Free-Fall Parachuting Tactics, Techniques, and Procedures. 18 February
1993.
FM 34-1. Intelligence and Electronic Warfare Operations. 27 September 1994.
FM 34-10-7. Quick Fix Operations. 30 September 1991.
FM 57-220. Basic Parachuting Techniques and Training. 1 June 1990.
FM 57-230. Advanced Parachuting Techniques and Training. 13 September 1989.
International Standardization Agreement
STANAG 3114 (Edition Six)/Air Standard 60/16. Aeromedical Training of Flight Personnel. 22
October 1986.
Soldier's Training Publication
STP 8-91B25-SM-TG. Soldier's Manual and Trainer's Guide: MOS 91B, Medical NCO, Skill
Levels 2/3/4/5. 17 July 1990.
Technical Bulletin
TB MED 289. Aeromedical Evaluation: A Guide for Health Care Providers (AFP 164-4;
NAVMED P5115; CG 436). 19 September 1986.
Technical Manuals
TM 5-4220-202-14. Maintenance Instructions with Parts Breakdown: USAF Flotation
Equipment (TO 143-1-102). 1 April 1986.
TC 1-212
References-3
TM 10-1670-201-23. Organizational and Direct Support Maintenance Manual for General
Maintenance of Parachutes and Other Airdrop Equipment. 30 October 1973.
TM 11-1520-237-23-1. Aviation Unit and Intermediate Maintenance for UH-60A Utility
Helicopter (NSN 1520-01-035-0266) (EIC:RSA) General Information, Navigational, and
Command Instrument Sets. 15 June 1994.
TM 11-1520-237-23-2. Aviation Unit and Intermediate Maintenance for UH-60A Utility
Helicopter (NSN 1520-01-035-0266) (EIC:RSA) Automatic Flight Control Set. 15 June
1994.
TM 11-1520-237-23-3. Aviation Unit and Intermediate Maintenance Avionics Maintenance
Task Manual for UH-60A Utility Helicopter (NSN 1520-01-035-0266) (EIC:RSA)
Communication Sets. 15 June 1994.
TM 11-1520-237-23-4. Aviation Unit and Intermediate Maintenance for UH-60A Utility
Helicopter (NSN 1520-01-035-0266) (EIC:RSA) Aircraft Survivability Equipment and
Appendixes. 15 June 1994.
(S) TM 11-5810-262-10. Operator's Manual for Speech Security Equipment KY-58 (U). 1 May
1990.
TM 11-5810-292-13&P. Operators, Unit and DS Maintenance for Electronic Transfer Device,
KYK-13. 31 May 1989.
TM 11-5810-301-13&P. Operators, Organizational and DS Maintenance for Electronic Key
Generator, TSEC/KG-45. 30 November 1984; change 1, 26 August 1988.
TM 11-5820-237-23-P Aviation Unit and Intermediate Repair Parts and Special Tools List
(Including Depot Maintenance Repair Parts and Special Tools) for Army Model UH-60A
and UH-60L Helicopter Systems. 15 July 1994.
TM 11-5841-283-12. Aviation Unit Maintenance Manual for Radar Signal Detecting Set,
AN/APR-39(V). 9 August 1983.
TM 11-5841-291-12. Operator's and Organizational Maintenance Manual (Aviation Unit
Maintenance) for Radar Warning Systems, AN/APR-44(V)1 and AN/APR-44(V)3. 14
April 1983.
TM 11-5855-238-10. Operator's Manual for Night Vision Goggles Ground Use: AN/PVS-5,
AN/PVS-5A, AN/PVS-5B, and AN/PVS-5C. 15 May 1993.
TM 11-5855-263-10. Operator's Manual for Aviator's Night Vision Imaging System, AN/AVS6(V)1 and AN/AVS-6(V)2. 1 March 1994.
TM 11-5855-300-10. Operator's Manual for Heads Up Display AN/AVS-7 (5855-01-350-0349)
(EIC:N/A)(NAVAIR 16-35HUD-2). 1 August 1994.
TM 11-5865-200-12. Operator's and Aviation Unit Maintenance Manual for Aviation Unit
Maintenance (AVUM) Countermeasures Sets, AN/ALQ-144A(V)1 and AN/ALQ-144(V)3.
15 July 1991.
TM 11-5865-201-12. Operator's and Aviation Unit Maintenance Manual for Countermeasures
Set, AN/ALQ-156(V)1. 5 March 1984.
TM 11-5865-202-12. Operator's and Aviation Unit Maintenance Manual for Countermeasures
Sets, AN/ALQ-136(V)1 and AN/ALQ-136(V)5. 1 August 1986.
TM 11-5865-229-12. Operator's and Aviation Unit Maintenance Manual for Countermeasures
Set, AN/ALQ-162(V)2. 30 November 1990.
TM 11-5895-1199-12. Operator's and Organizational Maintenance Manual for Mark XII IFF
System (AN/APX-100; AN/APX-72). 1 July 1984.
TM 55-1500-342-23. Army Aviation Maintenance Engineering Manual for Weight and
Balance. 29 August 1986.
TC 1-212
References-4
TM 55-1680-317-23&P. Aviation Unit and Aviation Intermediate Maintenance Manual with
Repair Parts and Special Tools List for Army Aircraft Survival Kits. 26 March 1987.
TM 55-1680-351-10. Operator's Manual for SRU-21/P Army Vest, Survival (Large and Small).
22 April 1987.
DOCUMENTS NEEDED*
The most current edition of these documents must be available to the intended users of this
publication.
Army Regulations
*AR 40-8. Temporary Flying Restrictions Due to Exogenous Factors. 17 August 1976.
*AR 95-1. Aviation: Flight Regulations. September 1994.
*AR 95-2. Aviation: Air Traffic Control, Airspace, Airfields, Flight Activities, and Navigational
Aids. 10 August 1990.
*AR 95-27. Operational Procedures for Aircraft Carrying Hazardous Materials. 11 November
1994.
*AR 600-105. Aviation Service of Rated Army Officers. 1 December 1983.
*AR 600-106. Flying Status for Nonrated Army Aviation Personnel. 2 March 1992.
Department of the Army Forms
DA Form 759. Individual Flight Record and Flight Certificate - Army. August 1993.
DA Form 2028. Recommended Changes to Publications and Blank Forms. 1 February 1974.
DA Form 2408-12. Army Aviator's Flight Record. January 1992.
DA Form 2408-13. Aircraft Status Information Record. October 1991.
DA Form 2408-13-1. Aircraft Inspection and Maintenance Record. October 1991.
DA Form 2696-R. Operational Hazard Report. March 1983.
DA Form 5484-R. Aircrew Mission Briefing. November 1985.
DA Form 5701-R. UH-60/AH-64 Performance Planning Card. September 1992.
Department of the Army Pamphlet
*DA Pamphlet 738-751. Functional Users Manual for The Army Maintenance Management
System-Aviation (TAMMS-A). 15 June 1992.
Department of Defense Flight Information Publications
Army Aviation Flight Information Bulletin
Flight Information Handbook
DOD flight information publications are available from Director, US Army Aeronautical
Services Agency, ATTN: MOAS-AI, Cameron Station, Alexandria, VA 22304-5050.
Department of Defense Regulation
TC 1-212
References-5
DOD 7000.14-R. Volume 7, Part A, Department of Defense Military Pay and Allowances
Entitlements Manual. 1 January 1993.
DOD 7000.14-R. Volume 7, Part B, Department of Defense Military Retired Pay Manual. 30
November 1992.
Department of Defense Forms
DD Form 175. Military Flight Plan. May 1986.
DD Form 365-4. Weight and Balance Clearance Form F--Transport. April 1989.
Federal Aviation Administration Publications
Airman's Information Manual.
FAR, Part 91. General Operating and Flight Rules.
FAR, Part 105. Parachute Jumping.
FAA publications are available from Director, US Army Aeronautical Services Agency, ATTN:
MOAS-AI, Cameron Station, Alexandria, VA 22304-5050.
Field Manuals
FM 1-109. Aviation Self-Deployment Planning. 29 May 1987.
*FM 1-112. Tactics, Techniques, and Procedures for the Attack Helicopter Battalion. 21
February 1991.
__________________
*This source also was used to develop this publication.
*FM 1-116. Tactics, Techniques, and Procedures for the Air Cavalry/Reconnaissance Troop. 20
February 1991.
*FM 1-203. Fundamentals of Flight. 3 October 1988.
*FM 1-301. Aeromedical Training for Flight Personnel. 29 May 1987.
*FM 1-400. Aviator's Handbook. 31 May 1983.
*FM 1-402. Aviator's Recognition Manual. 6 August 1984.
*FM 25-101. Battle Focused Training. 30 September 1990.
*FM 55-450-2. Army Helicopter Internal Load Operations. 5 June 1992.
*FM 55-450-3. Multiservice Helicopter External Air Transport: Basic Operations and
Equipment. 11 February 1991.
*FM 55-450-4. Multiservice Helicopter External Air Transport: Single-Point Rigging
Procedures. 11 February 1991.
*FM 55-450-5. Multiservice Helicopter External Air Transport: Dual Point Load Rigging
Procedures. 11 February 1991.
*FM 90-4. Air Assault Operators. 16 March 1987.
*FM 100-2-3. The Soviet Army Troops, Organization, and Equipment. 6 June 1991.
Memorandum of Understanding
Army/Air Force Deck Landing Operations Memorandum of Understanding Between the
Department of the Navy and the Departments of the Army and Air Force. July 1988.
TC 1-212
References-6
Training Circulars
*TC 1-201. Tactical Flight Procedures. 20 January 1984.
*TC 1-204. Night Flight Techniques and Procedures. 27 December 1988.
*TC 1-210. Aircrew Training Program: Commander's Guide. 3 October 1995.
TC 21-24. Rappelling. 24 September 1991.
Technical Manuals
*TM 1-1500-328-23. Aeronautical Equipment Maintenance Management Policies and
Procedures. 28 February 1995.
*TM 1-1520-237-1. Aviation Unit and Intermediate Maintenance for Army Models UH- 60A
Helicopters, UH-60L Helicopters, and EH-60A Helicopters. 31 August 1994.
*TM 1-1520-237-2. Aviation Unit and Intermediate Maintenance for Army Models. 31 August
1994.
*TM 1-1520-237-3. Aviation Unit and Intermediate Maintenance for Army Models. 31 August
1994.
*TM 1-1520-237-4. Aviation Unit and Intermediate Maintenance for Army Models. 31 August
1994.
*TM 1-1520-237-5. Aviation Unit and Intermediate Maintenance for Army Models. 31 August
1994.
*TM 1-1520-237-6. Aviation Unit and Intermediate Maintenance for Army Models. 31 August
1994.
*TM 1-1520-237-7-l. Aviation Unit and Intermediate Maintenance for Army Models. 31
August 1994.
*TM 1-1520-237-7-2. Aviation Unit and Intermediate Maintenance for Army Models. 31
August 1994.
*TM 1-1520-237-8. Aviation Unit and Intermediate Maintenance for Army Models. 31 August
1994.
*TM 1-1520-237-10. Operator's Manual for Army Models UH-60A Helicopters, UH-60L
Helicopters, and EH-60A Helicopters. 31 August 1994.
ê*TM 1-1520-237-CL. Operator's and Crewmember's Checklist for Army Models UH-60A
Helicopters, UH-60L Helicopters, and EH-60A Helicopters. 31 October 1996.
*TM 1-1520-237-MTF. Maintenance Test Flight Manual for Army Models UH-60A Helicopter,
UH-60L Helicopter, and EH-60A Helicopter. 31 August 1994.
*TM 1-1520-237-T-1. Aviation Unit Maintenance Fault Isolation Procedures Manual for Army
Models UH-60A Helicopters, UH-60L Helicopters, and EH-60A Helicopters. 31 August 1994.
*TM 1-1520-237-T-2. Aviation Unit Maintenance Fault Isolation Procedures Manual for Army
Models UH-60A Helicopter, UH-60L Helicopter, and EH-60A Helicopter. 31 August 1994.
*TM 1-1520-237-23P-1. Aviation Unit and Intermediate Maintenance Repair Parts and Special
Tools List (Including Depot Maintenance Repair Parts and Special Tools) for Helicopter
Utility Tactical Transport, UH-60A (NSN 1520-01-035-0266), EH-60A (1520-01-082-0686),
UH-60L (1520-02-298-4532). 28 February 1995.
*TM 1-1520-237-23P-2. Aviation Unit and Intermediate Maintenance Repair Parts and Special
Tools List. 28 February 1995.
*TM 1-1520-237-23P-3. Aviation Unit and Intermediate Maintenance Repair Parts and Special
Tools List. 28 February 1995.
*TM 1-1520-237-23P-4. Aviation Unit and Intermediate Maintenance Repair Parts and Special
Tools List. 28 February 1995.
TC 1-212
References-7
ê*TM 1-1520-253-10. Operator's Manual for UH-60Q Helicopter/HH-60L Helicopter. 29
January 1999.
ê*TM 1-1520-253-CL. Operator's and Crewmember's Checklist for UH-60Q Helicopter/
HH-60L Helicopter. 29 January 1999.
*TM 32-5865-012-10. Operation Instructions for Special Purpose Countermeasures System,
AN/ALQ-151(V)2. 26 April 1988.
*TM 55-2840-248-23. Aviation Unit and Intermediate Maintenance Manual for Engine,
Aircraft, Turboshaft, Models T700-GE-700 and T700-GE-701, and T700-GE-701C (TO
2J-T700-6). 28 April 1982.
READINGS RECOMMENDED
This reading contains relevant supplemental information.
Field Manual
FM 25-100. Training the Force. 15 November 1988.
__________________
*This source also was used to develop this publication.
TC 1-212
Index-1
INDEX
This index is organized alphabetically by topics and subtopics identified by page
numbers.
Academic training. See Training, academic.
Actions on contact, 5-4, 6-98
Aerial radio relay, 5-4, 6-97
After-landing tasks, 2-2, 7-10
Aircraft preparation for mission, 5-5, 6-99
Aircraft refueling, 5-4, 6-48
Aircraft survivability equipment, 5-4, 6-71
Airspace surveillance, 5-2, 5-4, 6-30
Air Standard 60/16, vi, 6-1
ALSE. See Aviation life support equipment.
Annual flying-hour requirements, 5-1
Annual task and iteration requirements, 5-2 through 5-5
crew member mission tasks, 5-4, 5-5
flight medic mission tasks, A-1
maintenance test pilot tasks, 5-5, 7-1 through 7-10
nonrated crew member base tasks, 5-4
rated crew member base tasks, 5-2, 5-3
Approach
nonprecision, 5-3, 6-67
precision, 5-3, 6-68
VMC, 2-3, 5-3, 6-76
ASE. See Aircraft survivability equipment.
Autorotation RPM check. See Checks, autorotation RPM.
Aviation life support equipment, 5-2, 5-4, 6-29
Base task and annual iteration requirements. See Annual task and iteration requirements.
Base tasks, 2-2, 5-2 through 5-4
FI and SI, 5-1
flight medic, A-1 through A-8
rated crew member, 5-1 through 5-3
Before-flight tasks, 2-2
Briefing
crew mission, 2-3, 5-2, 5-4, 6-14
passenger, 5-3, 5-4, 6-60
Checks
aircraft shutdown, 2-3, 5-2, 5-4, 6-3
TC 1-212
Index-2
attitude/airspeed, 5-5, 7-9
autorotation RPM, 5-5, 7-9
beep trim, 5-5, 7-9
before-landing through engine shutdown checks, 5-5, 7-10
before MTF, 5-5, 7-2
before-starting engine, 5-5, 7-4
before-starting engine through before-leaving helicopter checks, 2-3, 4-2, 5-2, 5-4, 6-28
before-takeoff and hover, 5-5, 7-6
before-takeoff through climb checks, 5-5, 7-7
cruise, 5-5, 7-8
engine shutdown, 5-5, 7-10
engine-start, run-up, and before-takeoff, 7-4 through 7-7
hover power, 2-3, 5-2, 6-32
in-flight controllability, 5-5, 7-9
interior, 5-5, 7-3
maintenance test flight, 5-5, 7-2
maximum power, 5-5, 7-9
operational on ALSE, 5-2, 5-4
run-up and taxie, 5-5, 7-5
SAS (during flight), 5-5, 7-9
special/detailed procedures, 5-5, 7-9
stabilator at 120 KIAS, 5-5, 7-9
starting engine, 5-5, 7-4
takeoff through climb, 5-5, 7-7
takeoff and hover, 5-5, 7-6
Command instrument system operations, 5-3, 6-71
Communication, 5-5, 6-4 through 6-16, 6-109
Continuation training. See Training, continuation.
Crew briefing checklist, 6-15
Crew chief, 1-2
Crew coordination, 6-4 through 6-15
Crew mission briefing, 2-3, 5-2, 6-15
Crew station designation, 1-1, 5-1
êDA Form 5703-R, 6-19 through 6-26.15
Deceleration, 5-5, 6-108 See also Terrain flight deceleration.
ECCM. See Electronic counter-countermeasures.
EH-60 aircraft system qualification, 2-4
Electrical control unit/digital electronic control lockout, 5-3, 6-54
Electronic-aided navigation, 2-3, 5-3, 6-41
Electronic counter-countermeasures, 5-5, 6-109
Emergency
egress, 2-2, 2-3, 5-3, 5-4, 6-56
procedures, 2-2, 2-3, 5-3, 6-58
Engine failure, simulated
TC 1-212
Index-3
at altitude, 5-3, 6-52
at hover, 5-3, 6-51
Equipment identification, US or allied and threat, 5-5, 6-108
Evaluation
crew member flight, 8-2 through 8-8
debriefing, 8-8
flight, 2-2, 3-2, 3-3, 8-1, 8-2, 8-7, 8-8
grading considerations, 8-2
guidelines, 8-2 through 8-8
instrument flight, 3-2, 5-3 through 5-6, 8-3
introduction, 8-2, 8-3
maintenance test pilot task list, 5-5
maintenance test pilot, 7-1 through 7-10
oral, 8-2 through 8-7
principles, 8-1, 8-2
standardization flight, 5-3 through 5-8, 8-1, A-1, B-1
Evaluators, 8-1 through 8-3
instructor pilot, 1-1, 2-1, 5-1, 5-6, 6-2, 8-1, 8-3 through 8-6
instrument flight examiner, 1-1, 5-2, 8-1
maintenance test flight evaluator, 1-1, 4-1, 5-2, 8-1, 8-3 through 8-6
standardization instructor pilot, 1-1, 2-1, 8-1
Evasive maneuvers, 5-4, 6-3, 6-83
External load operations, 5-4, 6-93
FAC. See Flight activity categories.
Firing position operations, 5-4, 6-83 though 6-85
Flat turn or calibrated flight, 5-5, 6-112
Flight
activity categories, 4-1, 4-2, 5-1, 5-2, 5-6
evaluation. See Evaluation, flight.
flight with AFCS off, 5-3, 6-53
medic, 1-2, A-1 through A-8
planning
IFR, 5-3, 6-17
VFR, 5-3, 6-16
training. See Training, flight.
Fuel
before-takeoff check, 5-5, 7-6
extended range fuel system operations, 4-2, 5-5, 6-113
management procedures, 2-3, 5-2, 6-38
sample, 5-3, 5-4, 6-59
Ground taxi, 2-3, 5-2, 6-30
Hand and arm signals, 5-3, 5-4, 6-59
Holding procedures, 5-3, 6-63
Hover, 5-2, 6-32 through 6-34
TC 1-212
Index-4
Hovering flight, 2-3, 5-2, 6-33
Hover power check, 2-3, 5-2, 6-32
IE. See Evaluators, instrument flight examiner.
IFR flight planning, 6-17
Inadvertent IMC procedures, 2-3, 5-3, 6-69
Initial qualification, 2-1
Inspection preflight, 5-2, 5-4, 6-27,6-39
Instrument
flight evaluation. See Evaluation, instrument flight.
takeoff. See Takeoff, instrument.
Internal load operations, 5-4, 6-96
Internal rescue-hoist operations, 5-4, 6-88
IP. See Evaluators, instructor pilot.
Landing roll-on, 2-3, 5-3, 6-45
Low-level flight, 2-3, 6-101 through 6-106
Maintenance test pilot tasks, 7-1 through 7-10
Maintenance test pilot, 4-1, 7-1 through 7-10, 8-3, 8-4, 8-5. See also Evaluation,maintenance
test pilot.
additional or alternate aircraft, 4-2, 5-2
mission training, 4-2
tasks and annual iterations, 5-2 through 5-4
Masking, 5-5, 6-106
ME. See Evaluators, maintenance test flight evaluator.
Medical flight evaluation. See Evaluation, medical flight.
Medic tasks, A-1 through A-8
Mission essential task list, 1-1, 4-1
Mission-oriented protective posture, 5-6
Mission task and annual iteration requirements. See Annual task and iteration requirements.
Mission tasks, 4-1, 4-2
Mission training. See Training, mission.
MOPP. See Mission-oriented protective posture.
MP. See Maintenance test pilot.
Multiaircraft operations, 5-4, 6-85
Navigation
doppler, 2-3, 5-3, 6-41
electronic-aided, 2-3, 5-3, 6-41
GPS, 2-3, 5-3, 6-41
IINS, 2-3, 5-3, 6-41
LORAN, 2-3, 5-3, 6-41
OMEGA, 2-3, 5-3, 6-41
pilotage and dead reckoning, 5-2, 6-40
radio, 5-3, 6-62
statements, 6-8
TC 1-212
Index-5
terrain flight, 2-3, 5-5, 6-101
NBC. See Nuclear, biological, chemical.
Night
considerations, 3-3, 4-2, 6-4, 6-17, 6-27, 6-29, 6-30, 6-31, 6-34, 6-36, 6-39, 6-40, 6-43,
6-48, 6-49, 6-51, 6-52, 6-53, 6-54, 6-55, 6-59, 6-60, 6-70, 6-73, 6-76, 6-77, 6-80, 6-86, 6-88,
6-89, 6-92, 6-95, 6-99, 6-101, 6-103, 6-104, 6-106, 6-107, 6-108, 6-116, B-3, B-4,
B-6, B-9
flight, 5-1 through 5-6
tasks, 5-3 through 5-8
training
mission, 4-1, B-1 through B-10
qualification, 2-2, B-1
refresher, 3-3, B-1
Night vision goggles. See also Evaluation, standardization flight.
considerations. See Night considerations. 1-2, 2-2, 3-3, 4-1, 5-1 through 5-6, 6-3, 6-4
currency requirements, 5-1 through 5-6, 6-3
mission training, 4-1
qualification, 2-2, 2-3
initial, 2-3
EH-60 mission equipment, B-1
UH-60 additional aircraft, 2-3
refresher training, 3-2 and 3-3
tasks and iterations, 5-2 through 5-6
No-notice evaluation. See Evaluation, no-notice.
Nonprecision approach. See Approach, nonprecision.
Nonrated crew member, 1-2
Nuclear, biological, chemical
annual training requirements, 5-2 through 5-4, 5-6
tasks and iterations, 5-2 through 5-4
NVG. See night vision goggles.
OGE power, 6-4, 6-60, 6-82 through 6-85, 6-86 through 6-89, 6-91 through 6-95, 6-103 and
6-104, 6-106 through 6-108
Operations
command instrument system, 5-3, 6-71
ECU/DEC lockout, 5-3, 6-54
external load, 5-4, 6-93 through 6-95
hoist (patient), A-2
internal load, 5-4, 6-96
internal rescue-hoist, 5-4, 6-88
multiaircraft, 5-4, 6-85
paradrop, 5-4, 6-89
slope, 5-3, 6-47
stability, 5-4, 6-91
Oral examination, 8-2, 8-3
aerodynamics, 8-6
TC 1-212
Index-6
aeromedical factors, 8-5
aircraft emergency procedures and malfunctions, 8-4
ME and MP system operations (malfunction analysis and troubleshooting), 8-5
night mission operation and deployment, 8-7
operating limitations and restrictions, 8-4
regulations and publications, 8-3, 8-4
tactical and mission tasks, 8-6, 8-7
Paradrop operations, 5-4, 6-89
Passenger briefing, 5-3, 6-60
Patient, A-1, A-3 through A-8
restraint, A-1, A-7
tasks, A-3 through A-8
PC. See Pilot in command.
êPerformance planning card, 3-1, 5-2, 6-19 through 6-26.15. See also DA Form 5701-R
(unnumbered).
Pilot in command, 6-1, 7-1
Postaccident flight evaluation. See Evaluation, postaccident flight.
Postflight inspection, 5-3, 5-5, 6-28
PPC. See Performance planning card.
Precision approach. See Approach, precision.
Preflight inspection, 5-3, 5-5, 5-11, 6-39, 7-2
Preventive maintenance service, 6-49
Proficiency flight evaluation. See Evaluation, proficiency flight.
Qualification training. See Training, qualification.
Quick Fix, 5-5, 6-111
Tasks--voice intercept operation mission
aircraft net mission, B-2, B-6
AN/ALQ-151 (V)2 operation under unusual conditions, B-2, B-7
C-10026/USQ receiver control unit, B-2, B-5
countermeasures set, AN/TLG-17A, B-2, B-6
emitter using the AN/ALQ-151 (V)2, B-2, B-5
file management procedures, B-2, B-5
initialization and BITE procedures, B-2, B-4
INTEROP mission, B-2, B-8
key cryptographic systems, B-2, B-3
mission planning requirements, B-2, B-7
preflight inspection, power-up, shutdown, and postflight inspection on an AN/ALGB151 (V)2, B-2, B-3
Voice intercept operator training, B-1 through B-10
Radio
communication procedures, 5-3, 5-4, 6-4 through 6-13, 6-65
failure, 5-3, 6-66
homing, 5-4, 6-82
navigation. See Navigation, radio.
Rappelling, 5-4, 6-86
TC 1-212
Index-7
Rated crew member, 1-2
Readiness of crew member, 8-2, 8-3
Refresher training. See Training, refresher.
Refueling, 5-4, 6-48
Relaying of patient information, A-1, A-3
Roll-on landing, 5-3, 6-45
Run-up tasks, 2-2
Semiannual flying-hour requirements, 5-1
Sequencing and timing, 6-5
Simulated engine failure. See Engine failure, simulated.
Slope operations, 2-3, 5-3, 6-47
SP. See Evaluators, standardization instructor pilot.
Spatial disorientation, 8-6
Special/detailed procedures, 5-5, 7-9
Stabilator malfunction, 5-3, , 6-56
Stability operations, 5-4, 6-91
STANAG 3114, vi, 6-1
Standard crew terminology, 6-11 through 6-13
Tactical communication procedures, 5-5, 6-109
authentication, 6-110
MIJI, 6-110
visual methods (other), 6-110
Tactical report transmission, 5-5, 6-111
Takeoff
instrument, 5-3, 6-60
VMC, 2-3, 5-2, 6-35
Task
considerations, 6-3, 6-4
contents, 6-1 through 6-3, 7-1 through 7-10
Terrain flight, 2-3, 5-5, 6-3, 6-4, 6-100, 6-101, 6-103, 6-105, 6-108
deceleration, 2-3, 5-5, 6-108
mission planning, 2-3, 5-5, 6-100
navigation, 2-3, 5-5, 6-101 through 6-104
task, 5-5, 6-103 through 6-106
Training
academic, 2-1, 2-2, 2-4, 3-1, 3-2
continuation, 5-1 through 5-6
EH-60 mission equipment qualification, 2-4, B-1
flight, 2-1, 2-2, 2-4, 3-2, 3-3, 4-2
flight medic crew, A-1 through A-8
instrument refresher, 3-1, 3-2
mission, 1-1, 1-2, 4-1, 4-2, A-1, B-1
NBC, 5-2 through 5-4
qualification, 1-1, 2-1 through 2-4, A-1, B-1
Quick Fix voice intercept operator, B-1 through B-10
TC 1-212
Index-8
refresher, 1-1, 3-1 through 3-3, A-1, B-1
UH-60L series qualification, 2-3, 2-4
Unit trainer, 5-1, 6-3, 8-2, 8-7
Unmasking, 5-5, 6-106
Unusual attitude recovery, 5-3, 6-64
UT. See Unit trainer.
Vertical helicopter instrument recovery procedures, 2-3, 5-4, 5-5, 6-69, 8-4
VFR flight planning, 5-2, 6-16
Visual signaling techniques, 5-3, 5-5, 6-59, 6-109, 6-110
VMC approach. See Approach, VMC.
VMC takeoff, 2-3, 5-2, 6-35
Weight and balance, 2-2, 3-1, 5-2, 6-19
Wet bulb globe temperature, 5-6
Wire obstacle negotiation, 5-5, 6-105
Word distinctions, 1-1
UH-60 PERFORMANCE PLANNING CARD
For use of this form, see TC 1-212: The proponent agency is TRADOC.
DEPARTURE
AIRCRAFT GWT: lbs PA: / FAT: °C / °C
FUEL WEIGHT: lbs
STORES WEIGHT: lbs
DUAL-ENGINE SINGLE-ENGINE
#1 #2
SLING WEIGHT: lbs ATF: ETF: ETF:
ZERO FUEL WEIGHT: lbs TR: TR: TR:
MAX TORQUE AVAILABLE % % %
MAX ALLOWABLE GWT OGE / IGE /
GO/NO-GO TORQUE OGE / IGE % / %
MAX HOVER HEIGHT IGE ft
PREDICTED HOVER TORQUE % % %
MIN SE-IAS - W/O STORES / W/STORES kts / kts
REMARKS:
CRUISE
PA: ft FAT: °C MAX ANGLE: ° Vne-IAS: kts
DUAL-ENGINE SINGLE-ENGINE
#1 #2
TR: TR: TR:
MAX TORQUE AVAILABLE CT % % % %
MIN / MAX Vh - IAS kts/ kts kts / kts
CRUISE - IAS / TAS / kts/ kts
CRUISE / CONTINUOUS TORQUE %/ % %/ %
CRUISE FUEL FLOW pph pph
MAX END - IAS / TORQUE kts/ %
MAX RANGE - IAS / TORQUE kts/ %
MAX R/C - IAS / TORQUE kts/ %
MAX ALLOWABLE GWT lbs lbs
OPTIMUM IAS AT MAX ALLOWABLE GWT kts kts
MAX ALTITUDE - MSL ft ft
EMERGENCY SE - IAS kts
DA FORM 5703-R
ARRIVAL
LANDING GWT: lbs PA: ft FAT: °C
DUAL-ENGINE SINGLE-ENGINE
#1 #2
TR: TR: TR:
MAX TORQUE AVAILABLE % % %
PREDICTED HOVER TORQUE % % %
MAX ALLOWABLE GWT OGE / IGE /
MAX HOVER HEIGHT IGE ft
MIN SE-IAS - W/O STORES / W/STORES kts / kts
REMARKS:
PAGE 2, DA FORM 5703-R
PIN: 64854-001
作者: Dovil 时间: 2009-10-7 10:02:58
there seems something wrong.作者: 帅哥 时间: 2009-10-8 12:50:56
i didn't insert the pdf,now u can download it作者: archer_gz 时间: 2009-10-8 23:01:40
现在试试，看能否下作者: yuxh 时间: 2009-12-4 20:16:17
没看见附件。作者: wtoleader 时间: 2009-12-12 16:32:34
tai gaoji le作者: wilbert_hj 时间: 2009-12-14 10:51:41