| Der Crewchief
Join Date: Nov 2004 Location: Ansbach, Germany
Posts: 34,086
| Okay I have the manual translated. The manual appears just be a general over view of the aircraft and its basic systems. All the systems are covered in other manuals 11 in total including a manual on maintenance practices and how to remove and replace broken componants or repair th aircraft. There is another manual that covers the MW power boost system. This manual covers the basic layout of it and where it is located in the aircraft but nothing about the operation of it.
Anyhow here is my translation of the manual. I have indicated where the figures would be in the document but you have to refer to the original document to see them. Also do to the fact that German can not be translated into English word for word this is just a rough translation. To the other German speakers here, I would love to have you correct any mistakes that I have made since there are probably quite a bit.
Here is the translation: Quote:
D (air) T. 2109 K-4 part of 9A only for the official use! BF 109 k 4 airplane manual
Part 9A general Ausrustung (conditions October 1944) edition December 1944
This is a secret article. Misuse is punishable.
Pg. 2
Table of Contents of the airplane manual
Part 0 general instructions supplement
1: General removal and reinstallation
2: chassis
3: tail unit
4: control mechanism
5: wing unit
6: power plant
7: engine serving and supply system
7a: fuel additive system
7b: MW system
8a: firing weapons (machine guns/cannon)
trunk armament Ñ s. L data processing T. 2109 K/Wa supplement
Wing suspended weapons system MG-151 s.L.Dv.T.2109K/Wa supplement
8b: released weapon system
9a: general equipment
9b: Electical system
Book 1: Description
Book 2: schaltunterlagen (can not think of english word for this)
9c: Pressure system
9d: on-board radio communication system
9e: Special tools and equipment
10: Salvaging
11: Instructions for repairing Ñ to s. D (air). T. 2109/Rep.
Pg. 3
D (air) T. 2109 K-4 part 9A
Only for the official use!
BF 109 k 4 airplane manual
Part 9A general equipment
(Conditions October 1944) Edition December 1944
Pg. 4
Supreme command of the Air Force
Chief of the technical Aerial Equipment
Test site D Lw. Rechlin
E2 NR. 280535/44 (V) edition December 1944
Rechlin, 29 December 1944
Hereby I approve the D (air) to:
"Bf-109 K-4" part 9 A Ñ N. f. D Ñ ÒBf 109 K-4 airplane manual part of 9 A: General Equipment
(conditions October 1944) edition December 1944.
It takes effect the day of publication.
IN GENERAL Wittmer
Pg. 5
Contents
I.
Instrument Panel. . . . . . . . . . . . . . 5
A. Description. . . . . . . . . . . . . 5
B. Removal and reinstalling. . . . . . . . . . . . . 5
II.
Engine monitering equipment (instruments). . . . . . . 9
A. Description. . . . . . . . . . . . . 9
1. manifold pressure indicators. . . . . . . . . . . 9
2. tachometers. . . . . . . . . . . . 9
3. propellers - flaps position indicators. . . . . . . 9
4. mackle measurers. . . . . . . . . . . 9
5. lubricate - and cooling system providers. . . . . . . .10
6. temperature indicators fŸr lubricate - and cooling system provides. . . . . . 10
7. Vorratsgeber (can not think of english word for this something to do with supply and giving . . . . . . . . . . . . . 10
8. Fuel indicators . . . . . . . . 10
9. Fuel Low warning light . . . . . . . . . 10
10. Pressure gauge for MW system. . . . . . . . 10
III.
Flight instruments and Navigation Equipment. . . . . . . . . . . . . . 13
A. Description
1. airspeed indicators. . . . . . . . . . . . . 13
2. pitot tube. . . . . . . . . . . . . . 13
3. altitude indicators (I think). . . . . . . . 13
4. Vertical Speed indicator. . . . . . . . . . . . . 13
5. Ausgleichsgefass (I can not find an english word for this either I'm probably just stupid) . . . . . . . . . . . . 13
6. Mother compass (main) . . . . . . . . . . . 14
7. Secondary compass. . . . . . . . . . . 14
8. Artificial Horizon. . . . . . . . . . . . 17
9. transformers. . . . . . . . . . . . . . 17
IV.
High Alltitude Oxygen system.. . . . . . . . . . . 19
A. Description . . . . . . . . . . . . 19
B. Removal and Reinstalling . . . . . . . . . . . . 19
C. Operating Instructions . . . . . . 21
D. Servicing . . . . . . 21
E. Inspections . . . . . . 22
F. Storing . . . . . . 22
V.
Survival and Safety Equipment. . . . . . 23
A. Description. . . . . . 23
1. seat belts. . . . . . . . . . . . 23
2. Water survival Equipment. . . . . . . . . . . 23
3. Emergency Landing Equipment. . . . . . . . . . . 23
4. flare gun. . . . . . . . . . . . . 23
VI.
Fuel Disk Rinsing (not sure on this one).. . . . . . . . 24
A. Discription.. . . . . . . . 24
B. Removal and Reinstalling.. . . . . . . . 25
C. Inspections and Storage.. . . . . . . . 25
VII.
Armored Disk Heating . . . . . . . . . 26
A. Description . . . . . . . . . 26
Pg. 6
Illustrations
Fig.1: Instrument placement in the cockpit. . . . . . . . . 7
fig.2: Landing gear instrument system. . . . . 11
fig.3: Flight instruments. . . . . . 14
fig.4: Navigation as well as the survival and Safety equipment.. . . . . . . . . . . . . . . 15
fig.5: Mother compass (main). . . . . . . . . . . . . 17
fig.6: Layout of High Altitude Oxygen System.. . . . . . . . 18
fig.7: Overview of the oxygen producing system. . . . . . . . . 20
fig.8: Cockpit instruements on the right. . . . . . 21
fig.9: Overview of the fuel disk rinsing (not sure of this one). . . . . 24
Pg. 7
I.
Instrument Panel
A. Description
The Instrument Panel is arranged with the required Engine instruments -, flight instruments and Navigation equipment.
The Instrument Panel is secured with hexagonal screws at the Instrument Panel mount, which is bolted with the front part of the structure
for wind protection. On the Instrument Panel also are the instruments for machine guns and cannons and the
pressure gauge are for the MW plant arranged (see to part 7 B). At the lower edge of the Instrument Panel are the
emergency instruments as well as the Mk-108 safety.On Emergency instruments panel is where the ZSK 244 A is arranged (s. part of 8 A).
Particularly sensitive instruments are: AFN 2-instrument, rate of climb indicator, artificial horizon, airspeed indicator, Altimeter
and Secondary compass are used for blind (instrument) flight and are built in rubber-bonded metal instrument panels on the main instrument
panel.
B. Removal and Reinstallation
Before removing the Instrument panel remove the Emergency Instrument panel; first by removing the bolting device and then the
mounting plate at the Instrument panel. Disconnect Electrical Cannon plugs on the backside of the Instrument Panel, the
Emergency Instrument Panel and the ZSK 244A in the cockpit. Likewise in the same way remove the blind flight (instrument) board
from the Instrument Panel. Then on the backside remove the elictrical lines, Electrical cannon plugs, pipings and flexible waves from
the instruments on the instrument panel. Remove the Instrument Panel after removing the 4 fixing bolts.
When clamping the electrical lines for security keep in mind whether the vein ends are provided
with terminal markings! Tubing and hose ends as well as... openings for the instruments must be protected against contamination
cover them. (caps, material etc.).
Pg. 8
The installation of the instrament panel board takes place likewise in reverse order. The equipment is to be inserted before the
installation of the instrument panel. The attachment of the panel on the instrument board takes place almost completely via
fillister-head screws, which are screwed into anchor nuts (riveted on the reverse side of the instrument board). By tightening
the fixing bolts to it, make sure the screws are equally tightened, so that the instrument does not jump. The limit
value markings are to be indicated on the instrument by pointers or by red marking lines.
Pg. 9-10 are Illustrations see original document
Pg. 11
II.
Engine Instruments
A. Description
For engine monitoring are the following instruments installed (see fig. 2):
1 manifold pressure indicator (fig. 2/1)
1 tachometer (fig. 2/2)
1 propeller flaps position indicator (fig. 2/3)
1 oil pressure indicator (fig. 2/4)
1 oil tempereture transmitter (fig. 2/5)
1 cooling system temperature transmitter (fig. 2/6)
1 Oil temperature indicator (fig. 2/7)
1 temperature indicator fŸr lubricant (fig. 2/7)
1 fuel pressure indicator (fig. 2/9)
1 fuel quantity indicator (fig. 2/10)
1 fuel low warning indicator (fig. 2/11)
1 pressure gauge fŸr MW system (fig. 2/12).
Managing the Engine Instruments is further covered in section 6, where also the instruments are shown.
Covering impact, removal and installation, inspections, and maintenance of the Engine Instruments and components
D. (air) T.
1. Manifold pressure indicator
The manifold pressure indicator with a range from 0,6 to 1.8 ata is down on the right side of the instrument panel. The
pressure sensor is attached to the trunk bulkead of the cockpit to the loader pipe of the engine.
2. Tachometer
For the speed measurement is the mechanical tachometer with a range from 500 to 3500 U/min on the right side of the instrument panel.
The drive takes place via a two-piece flexible wave, which is connected with the tachometer drift to the mechanical motors backside.
3. Propeller flaps position indicator
The propeller flaps position indicator for the indication of the sheet position of the propeller is arranged beside the
tachometer on the instrument panel. This flaps position indicator is a winkeltrieb (can not find english translation) connected with the
Einheitsverstellgeret (can not find english translation of this) arranged in front under the engine by means of flexible wave.
4. Pressure Indicator
For the strength and oil pressure measurement is arranged a mackle measurer inserted right above the instrumetn panel and
with one pointer each for strength and oil pressure provided. The pressure acceptance takes place at the fuel feeding pump
and/or at the
Pg. 12
oil filter. At the indication sensor connection at the engine a safety throttle is inserted into the feul pressure sensor.
5. Oil and Cooling System Temperature provider
The provider for the oil temperature is inserted in the Kruemmer (not sure of the english word for this) of the lubricant advance line and the provider for Cooling
System temperature into the steam separator of the right side of the engine block. (not even sure if I got this whole sentance right)
6. Oil and Cool System Temperature Indicator
The Electrical temperature indicator for oil as well as the temperature indicator for the Cooling System are on the top right of the Instrument Panel. The
temperature indicator for oil indicates the inlet temperature and the temperature indicators for Cooling System indicates the outlet temperature.
7. Supply Giver (not sure if I got that right)
The supply giver is built on the cover of the Hauptbeholterkopfes (not sure what it is in English) into the Fuel Cell. The supply giver is provided with a sensor for the
Fuel Low warning; it steers the ELT supply indicator and switches the Fuel Low Light.
8. Fuel Quantity Indicator
The quantity indicator for the fuel is arranged on the bottom right of the instrument panel. An exact indication only takes place in flight attitude.
9. Fuel Low Warning Light
The Fuel Low Warning Light is located on the bottom right of the instrument panel. The light illuminates, if the fuel quantity in the Fuel Cell is
only sufficient for flight time of approximately 10 minutes.
10. MW System Pressure Indicator
The pressure indicator for the MW power boost system is located in the upper right of the instrument panel. (see A. Part 7B.)
Pg. 13 is illustrations see original document
Pg. 14 is blank.
Pg. 15
III.
Flight Instuments and Navigations Equipment
A. Description
Flight Instruments
The following flight instruments are installed (see fig 3):
1 Airspeed indicator
1 Heatable pitot tube
1 Altitude Indicator
1 rate of climb indicator
1 Ausgleichsgefass (not sure of translation for this)
Also a clock is installed.
1. Airspeed Indicator
The airspeed indicator with a range from 100 to 900 km/h is located on the upper left of the blind flight (instrument flight) board.
2. Heatable Pitot Tube
The heatable pitot tube serving for the airspeed indication is inserted in the edge cap of the left wing. Readings of the stagnation pressure
and static pressure on the airspeed indicator takes place via pipings.
3. Altitude Indicator
The Altitude Indicator is located on the blind flight (instrument flight) board underneath the airspeed indicator. It has a Above Ground and
above sealevel indicators with a range from 0 to 10000 m. The instrument is connected with the static pressure balance line.
4. Rate of climb indicator (Vertical Speed Indicator)
For the rate of climbing and of the rate of descent of the airplane is on the top right inserted on the blind flight (instrument flight) board a rate of climb indicator.
The rate of climb indicator is on the one hand attached to the static pressure balance line and on the other hand to the Ausgleichsgefass (not sure of translation).
5. Ausgleichsgefass (not sure of translation for this)
The Ausgleichsgefass (not sure of translation for this) for the rates of climb indicator is arranged and with Spannbandern (not sure of translation) fastened to two mounting plates
in the trunk before the instrument panel, those screwed onto the Z-profile of the front trunk cover. Ausgleichsgefass attached.
Pg. 16
Navigations Equipment
The following Navigations Equipment is installed (see fig. 4):
1 Mother compass (main)
1 Secondary compass
1 Artifical Horizon
1 Transformer
6. Mother Compass (main)
The Mother compass (main) is attached within the range of the trunk part 5 in a mounting plate secured with springs in the fuselage end section. Starting from serial no........
the Mother compass (main) is in the trunk part 5 above and with instructions in the trunk part of 6 inserted and electrically connected with the secondary compass above and steers its course rose.
7. Secondary Compass
The secondary is down on the blind flight (instrument flight) board on the Instrument Panel. It is a Navigation compass with a course rose electrically steered by the mother compass for course announcement.
Pg. 17 is illustrations see original document.
Pg. 18 is blank.
Pg. 19
8. Artificial Horizon
The artificial horizon indicated the attitude of the airplane in relation to the ground and sky, and is installed in the blind flight (instrument flight) board on the Instrument Panel.
9. Transformer
The transformer serves for the drive of the artificial horizon and is installed before the Instrument Panel at the left trunk sidewall.
Pg. 20 is Illustrations see original document for that.
Pg. 21
IV.
High Alltitude Oxygen System
A. Description
For the High Alltitude Oxygen System the following Equipment is installed:
3 oxygen supply bottles (ball bottles)
1 Jerk blow valve
1 Outboard Connection with stop valve
1 Steer round High Altitude breathing device
1 through-way valve
1 O2 regulator*
1 Pressure Indicator*
*Replace by O2 indicator
The arrangement of the equipment is shown in fig. 7.
The 2-Ltr. Oxygen ball bottles are fastened and within the range of the ribs 10 to 12 in the right wing accommodated on two mounts. Between the ribs is a stiffening board and is fastened 10a and 10,
at which the mount is placed.
The system is filled by an outside fill port that is accessable through a panel on the underside of the wing.
In order to avoid safety hazards of a leak of the oxygen through the outside fill port, a stop valve is installed at the Full line and between the outside fill port and the oxygen cylinders a pressure vent
inserted.
Steer round High Alltitude Breathing device, pressure gauges, O2-gauges and through-way valve are installed in the equipment storage in the cockpit.
The oxygen supply takes place in the normal way via the reversible High Alltitude breathing device of the oxygen system with a opened through-way valve. The pressure gauge indicates the oxygen pressure in the system and the O2-guage
insures the correct working of the oxygen system. With an automatic oxygen controler installed the UH breathing device supplies pure oxygen starting from 8000 m.
The tubes of the plant are painted blue and marked at the ends provided with white rings and/or by recognition bands.
B. Removal and Reinstallation
Caution!
When Removing and Reinstalling the High Alltitude Oxygen System caution must be taken so as not to contiminate the system with oil or grease.
Before the dismantling, the oxygen is to be discharged as follows:
Loosen closed through-way valve screw connection behind the through-way valve or at the breathing device. Then slowly open the through-way valve at the Equipment box and allow the CO2 to escape. Only after complete emptying of the system, unscrew the fitting.
Remove the bottles from the mounts.
Pg. 22 is illustrations see original document
Pg. 23
For the dismantling of the Equipment Container, first remove the cover of the panel bench beside the Equipment Container. From this the fitting and the fixing bolts of the Equipment Container are to be taken out to Remove the Container.
For Reinstalation follow the directions in reverse order.
Caution!
Pay attention to the correct installation of lines, correct enlargement of the thrust ring aswell as correct bolting!
C. Operating the High Altitude Oxygen System
Before takeoff put the breathing mask on and test the system. Starting from an alltitude of 4000m use the breathing device; to do this open the through-way valve. Observe the Pressure gauges and O2-guages (particularly when taking fire!).
To test for leaks bend the breathing mask and hold together.
With a higher breathing resistance or breathing difficulty push the respiration push button breafly several times.
When done using the system close the respiration 2 way valve.
Pg. 24
D. Servicing the High Alltitude Oxygen System
To fill the Oxygen System open the access panel under the wing to the outside fill port. Slowly release Pressure. Connect the High-pressure hose of the Oxygen fill tank to the outside fill port and open the stop valve.
After the stop valve has been opened fill the bottle to 165atu (pay attention to the pressure gauges!).
When the bottle are filled to the appropriate pressure close the stop valve and remove the high pressure hose and close the access panels.
Caution! Keep all components oil and grease free.
E. Inspections
Check to see that the system is in perfect working condition and inspect all attachments in accordance with s. D. (air) 1205.
Check for cleansliness of breathing hoses.
Dirt and Water build up in the oxygen cylinders are to be removed by blowing out with oxygen. To do this separate the fittings close to the bottles.
Afterwards recconect the fittings to the bottles
Quick Inspection:
Open the Throughway Valve, read off the oxygen pressure and then close the Throughway Valve. Pressure may drop in 20 minutes no higher than 20 atu.
Inspecting the whole System
Open the valve and read off the pressure. The pressure must be atleast 100atu. Allow the system to remain under pressure for several hours. The Oxygen pressure may drop no more than 10atu.
If the pressure drop is great check the system for leaks (soapy water). Pull the screw connections tight to prevent leakages and check wheather they enlarge perfectly.
If the lines are leaking they are to be replaced.
Inspection of the Breathing Device
Inspect with Leak Inspection Equipment FI 30453. If this Equipment is not available, then open the Throughway Valve until the highest pressure is reached. Close the Throughway valve.
The pressure may sink no more then 20atu in 20 min.
With a closed Throughway Valve confirm o2 shower. (? dont ask me, I am not sure if my translation here is correct) The Pressure gauges must fall at the same time and indicate the O2 gauges.
F. Storing
The pipings must be connected with the grounding electrode at the mating surfaces.
Fuel, oil, and grease are to be kept away from the system at all times.
Store the system in accordance with s. D. (Air) 1205 and D. (Air) T. 5210.
Pg. 25
V.
Survival and Safety Equipment
A. Description
1. Seatbelts
Attached at the seat are a lap strap and a shoulder belt for the pilot. Both belts have a quick disconnect for emergencies.
2. Water Survival Equipment
The pilot's seat is built in such a way as to accomadate a pilot with Distress Equipment (1 Man Life Boat and accessories), in accordance with D (air) T. 5204).
3. Emergancy Landing Equipment
In the fuselage tail section (by the man-hole cover), a crate is installed containing forced landing food supply and equipment.
4. Flare Gun
For ground location recognition a flare gun is inserted into the mounting plate to the Equipment cover. The flare are carried on the pilot in his equipment.
The arrangement of the rescue and safety equipment is shown in fig 4.
VI.
Fuel Disk Rinsing (not sure on this one)
A. Description
For the cleaning of the front disk of oil and grease is a Fuel Disk Rinsing device built in (see Fig 9). The confirmation of the Fuel Disk Rinse may only be
done in flight. (This does not make sense to me but I do not know any other way to translate it.)
The valve is opened by the lever installed left of the Equipment board; thus the fuel which is with the running engine in the piping while under pressure is
squirted by the jets of the jet cylinders arranged at the lower surface of the windshields at the disks. The fuel pipe for the front disk rinsing is attached
to the t-handle of the passage **** of the cold weather starting system (see part 7A).
Pg. 27
B. Removal and Reinstallation
The interface that is necessary with engine change is left of the engine. If the entire system is to be removed and/or replacemed, then this can be done itself
without special difficulties. Special attention must be paid during the reinstallation of the jet cylinders that they are secured to underside of the front disks
so that they will be rinsed simultaniously.
C. Storage and Inspection
The system of the Fuel Disk Rinsing is there to inspect whether the jets of the jet cylinders are not clogged, thereby, the front disk is cleaned
in flight after confirmation of the lever by fuel being sprayed. (really not sure of this one)
Pg. 28
VII.
Armored Disk Heating
A. Description
To protect against fitting and freezing the tank front disk can be heated electrically. The system is connected to the ELT electrical system and in
such a manner that by the brought in chassis the confirmation switch will switch to on securing the electric circuit.The system will not work on the ground.
(s. A. part 9 B, number 1). (not really sure on this whole translation of this section)
|
__________________  fly boy:"isnt that the first jet bomber becasue i have flown one in a flight sim before and i know how it handles" |
03-16-2005, 05:47 PM
Linear Mode
