TPG0005, Operating Guide for Pistion Rotorcraft

AIRCRAFT PRODUCTS
COLD WEATHER MODIFICATION
OPERATING GUIDE
Document No: TPG0005 Rev. C
Dated: JUN-15-2016
FOR
ROTORCRAFT
PREHEAT SYSTEM
Aircraft Registration:
Installed Preheat System Electrical Specifications:
Voltage:
Wattage:
Amperage:
Battery heat kit installed:
AV/Cabin Heater installed:
Yes
Yes
No
No
(This page and Appendix completed at time of installation)
PROPRIETARY DATA
Tanis Aircraft Products proprietary rights are included in the information disclosed herein. The recipient by accepting this document agrees that neither
this document nor the information disclosed herein nor any part thereof shall be reproduced or transferred to other documents or used or disclosed to
others for manufacturing or for any other purpose except as specifically authorized in writing by Tanis Aircraft Products - 952-224-4425.
Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
RECORD OF REVISION
When updated, this document is changed in its entirety.
REV
DATE
DESCRIPTION
BY
APPROVAL
C
JUN-15-2016
Add figures with layout and connection points
GDO
B
MAR-21-2014
Formatting change to Operating Guide
DNE
DNE
A
OCT-05-2010
Initial Release
DNE
N/A
Digitally signed by
dirk@tanisaircraft.com
DN: cn=dirk@tanisaircraft.com
Date: 2016.06.20 14:15:27
-05'00'
CONTENTS
RECORD OF REVISION ........................................................................................................... 2 CONTENTS ............................................................................................................................... 2 A. PURPOSE AND SCOPE ..................................................................................................... 3 B. GENERAL INFORMATION ................................................................................................. 3 1. Preheating ..................................................................................................................................... 4 2. Power Requirement ...................................................................................................................... 4 3. Power Connection ......................................................................................................................... 4 4. Power Connection and Placard..................................................................................................... 5 C. SYSTEM OPERATION ........................................................................................................ 7 1. Guidelines ..................................................................................................................................... 7 2. Control ........................................................................................................................................... 7 3. Preflight Procedures ...................................................................................................................... 7 4. Post Flight Operation .................................................................................................................... 8 D. WEIGHT AND BALANCE ................................................................................................... 8 E. HANDLING, SERVICING, AND MAINTENANCE ............................................................... 8 F. MALFUNCTION PROCEDURES ........................................................................................ 8 G. APPENDIX - INSTALLATION LOG .................................................................................... 8 Tanis Aircraft Products Data – Subject to warning on cover page.
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Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
A. PURPOSE AND SCOPE
The purpose of this guide is to provide instruction for the proper and safe use of the Tanis
Preheat System installed on this aircraft, and to aid the operator in complying with standard
aviation and airframe/engine manufacturer's procedures.
For specific instructions relating to engine starting and cold weather operations refer to
applicable POH (Pilots Operating Handbook) and/or AFM (Airplane Flight Manual), FAA
Advisory Circular - Cold Weather Operation of Aircraft AC No: 91-13C.
Instructional reference to other cold weather modifications, such as interior heaters, covers and
cowl plugs, are not part of this cold weather modification and are not included in this Operating
Guide. Weather planning and aircraft preparation are the responsibility of the operator.
This system does not change existing environmental flight restrictions.
B. GENERAL INFORMATION
Preheating is recommend at temperatures at/or below 0.0C / 32F. Manufacturers require
preheat when an engine has been cold soaked or exposed to a temperature with a wind chill
factor of -6.7C / 20F or below, for a period of 2 hours or more.
A cold soaked engine may start only to cause damage that shows up later. Rapid heating after
a cold start coupled with rapid expansion of parts and poor lubrication can damage or cause
excessive wear that can lead to poor engine and aircraft operation, premature repairs, overhaul,
or failure. Single point, inadequate, or superficial application of preheat does not evenly heat
internal parts or de-congeal oil throughout, engine, gearboxes, oil reservoirs and tanks.
The multi-point preheat system installed on this aircraft properly applies a thorough even
application of heat to critical driveline components, and fluids. Preheating increases reliability
and safety of operations reduces thermal stress, run-up, and launch times.
Figure 1 – Generic preheat system layout (TRGB element not used on some models).
Tanis Aircraft Products Data – Subject to warning on cover page.
Page 3 of 8
Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
1. Preheating
Preheating is accomplished through electrical resistance elements located on engine and
critical driveline components. Heated components reach an average state of thermal
equilibrium in six hours, with a temperature rise of approximately 33.33°C ± 5.56 / 60° F ±
10, over ambient air temperature. The preheat system is self-regulating by design. Timers
and thermostats are not used with the main system.
Battery heater (when installed) is controlled through a thermal controller that limits operation
of the battery element to temperatures below freezing.
AV/Cabin heater (when installed) is on anytime it is connected to power.
Power is routed through a dedicated wiring assembly with circuit protection (listed in Section
F), and red power indicator light.
2. Power Requirement
The system does not operate in flight, is not connected to or dependent on aircraft systems,
and is only capable of operation when connected to a ground based power source.
System design is for operation at plus or minus 10% of system voltage requirement.
A ground based power source capable of supplying or producing required voltage and load
for the duration of operation is required. This is commonly AC (alternating current).
The shore power plug and placard (Figures 1 and 2) identify system voltage. Specific
voltage and amperage requirements for the system installed are recorded on the cover
page. For detailed electrical values and maintenance information, reference recorded
documents in section G. Appendix.
3. Power Connection
Shore power and connection (extension cord), are the responsibility of the operator. 230volt systems are supplied with receptacle plug adapter (TP02829-230), for field installation
on extension cord supplied by operator. Extension cord is to be in good condition and of
adequate gauge to carry the total current draw of the system. A wire gauge of at least 16 is
recommended for an extension cord 50 feet or less in length (Table 1). A cord exceeding
100 feet is not recommended; if in doubt, use the next heavier gauge. The smaller the
gauge number, the heavier the cord. Note that an undersized cord will cause a drop in line
voltage and loss of power, along with possible overheating of the cord.
Table 1 - Extension cord specifications
Conductor
gauge/wires:
Maximum amps:
Maximum length:
16/3
13 A
50'
15 A
50'
13 A
100'
15 A
100'
15 A
100'
14/3
12/3
10/3
(Circuit protection 12-Amp fuses)
Tanis Aircraft Products Data – Subject to warning on cover page.
Page 4 of 8
Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
4. Power Connection and Placard
Shore/ground power connection point (inlet) is the Shore Power Plug. Locations vary by
installation. Placard with voltage requirement is located adjacent to shore power plug
(Figures 1 and 2).
Figure 2 - Plugs and placards. Alternate placard stating "TANIS" and voltage
requirement is acceptable.
Figure 3 - Shore power plug location varies by installation. Common location is on pilot
side with other shore connections or accessible through an inspection panel.
Figure 4 – Small piston powered helicopter preheat system plug commonly located on
the engine oil filler tube or airframe tubing (Figure 3). Note: TRGB jumper not
used on all models.
Tanis Aircraft Products Data – Subject to warning on cover page.
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Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
Figure 5 – Helicopter preheat system plug location varies by installation. Common
location is on pilot side of airframe with other shore connections or accessible
through inspection panel, or plug mounted on skin (TRGB jumper lead not used
on all models).
Figure 6 – R66 preheat system plug on pilot side accessible through an ELT access
door.
Tanis Aircraft Products Data – Subject to warning on cover page.
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Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
C. SYSTEM OPERATION
Caution: Do not touch hot elements as they can burn bare skin.
The aircraft is not to be fueled and engine is not to be operated while the system is
connected to shore power or extension cord (plugged in).
1. Guidelines
Use fluids and oils as recommended by the manufacturer for conditions of flight, and only
operate the preheat system with aircraft fluids at operational levels.
1.1. When available, follow specific preheat instruction provided by airframe and/or engine
manufacturer.
1.2. Design is for continual operation in all weather and temperature conditions while on
the ground.
1.3. For maximum benefit, system should be in continual operation for 6 hours or longer
before engine start (approx. temp. rise of 60°F / 33.33°C over ambient).
1.4. When operating at temperatures with a wind chill of -12°C / +10°F and below, the use
of insulated engine cowl cover is suggested. Available separately, insulated covers
increase efficiency by insulating and acting as windbreak.
1.5. When the system is connected to power, the red indicator light will turn on (illuminate),
and elements will begin to heat. Verify operation after about 30 minutes by reaching
into cowls and feeling for warmth.
1.6. When installed, the tailrotor gearbox element is commonly connected by a jumper lead
that is flagged with a streamer stating, “Remove Before Flight”. This lead is only
connected during preheat, and is disconnected and stowed before engine start-up.
Note: TRGB jumper is not required on all models.
2. Control
Connection to ground/shore power controls operation.
2.1. Activate system by connecting (plugging) to appropriate power.
2.2. Deactivate the system by disconnecting (unplugging) from power.
3. Preflight Procedures
Follow applicable aircraft Preflight Procedures and Check Lists, adding the following:
3.1. Remove engine and airframe cowl plugs and/or covers, if used.
3.2. Verify system has been in operation for the required period of time, check to see that
the power indicator light is on, and engine, main and tail rotor gearboxes feel warm.
When applicable check cockpit instrumentation readouts.
3.3. If used, disconnect tail rotor jumper flagged, “Remove Before Flight”.
3.4. Unplug/disconnect extension cord from aircraft.
3.5. Latch any access doors that were open.
3.6. Stow extension cord and tailboom jumper cable in appropriate location.
3.7. Start the aircraft following normal starting procedures.
Tanis Aircraft Products Data – Subject to warning on cover page.
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Operating Guide - Rotorcraft
TPG0005 Rev. C
JUN-15-2016
4. Post Flight Operation
Engine preheat system may be plugged in after full engine shut down.
4.1. Once the aircraft is secured, if used connect tail rotor gearbox heater jumper cable.
4.2. Plug the preheat system in and verify operation by checking power indicator light is on
(illuminated).
4.3. If used, install cowl plugs and/or covers per manufacturer’s instructions.
D. WEIGHT AND BALANCE
Equipment List and Weight & Balance figures recalculated at time of system installation.
E. HANDLING, SERVICING, AND MAINTENANCE
For detailed information regarding maintenance, installation and electrical values, refer to
specific installation instructions and ICA listed in the Appendix.
F. MALFUNCTION PROCEDURES
Should a malfunction be detected, such as tripped circuit protection (blown fuse), smoke, or lack
of heat, disconnect the system from power and placard (flag) as inoperative IAW applicable
regulations if eligible, or defer IAW approved MEL/NEF if applicable, and inspect before flight.
Repairs are to be conducted by appropriately rated and certified technician or
maintenance/repair facility.
For trouble shooting, inspection and repairs refer specific
installation instructions and ICA listed below.
For fuse replacement, disconnect system from power and replace fuses. For direct replacement
use Tanis part number TU02848, 12-Amp 1.25x.25 ceramic tube fuse. Acceptable alternates
are Bussmann ABC-12 or AGC-12.
G. APPENDIX - INSTALLATION LOG
Date of Installation:
Installed Preheat Kit(s):
Installation Instruction:
Document - Revision - Date
Instructions for
Continued Airworthiness (ICA):
Document - Revision - Date
(This page and the cover page completed at the time of installation)
***** NOTHING FOLLOWS ****
Tanis Aircraft Products Data – Subject to warning on cover page.
Page 8 of 8
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