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Name
Group
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
INSPECTIONS
�II
This outline is to be used as a study outline, notebook, and
inspection guide, and will remain the property of the student after
completion of the work. A complete set of notes will minimize the
need for references to the Technical Orders after the student is
in the field. Blank pages have been inserted in this book for the
convenience of the student in making notes.
Students are required to read and make notes of the Technical
Orders cited. A complete file of the Techn~al Orders is filed in
Room 215 and may be consulted there but may not be removed from
this room under any circumstances.
Wherever an inspection requires tools and facilities not adaptable to the flight apron, arrangements have been made to include
these inspections in the regular work in the classroom, laboratory,
or hangar. The inspection must be initialed by the instructor under
whom the work is done and who will see that the student has completed
the necessary work in a satisfactory manner. The place where these
inspections are to be carried out is indicated by asterisks:
** Inspection to
..,..*
Inspection to
~ • Inspection to
be made in the hangar
be made in the laboratory
be made in the classroom
Inspections not so marked will be performed on the flight apron
under the supervision of the inspection department.
Some inspections have been omitted from this outline because
they are not applicable to existing airplane models or because
these cover inspections not made at the school apron.
�III
INSPECTIONS
Inspection Type
Due Time
1. •PRE-FLIGHT"
Prior to the
first flight
each day
(Ready for flight
2•
11
DAILY"
(General
Condition)
3. 25 Hour
(Detection of
Slight Wear)
4. 50 hour
Maximum Intervals
Between Inspections
No Airplane will remain idle more than
six days without a
pre-flight inspection unless in "In
Storage" status;
undergoing engine
change; or in the
engin~ering shops
and not being used
for flight.
Either after No airplane will go
longer than six days
the day's
flying is
without a 11DAILrt.
over, or
before the
start of
flying the
following day.
Between the
20th and the
30th hour
after completion of the
last previous
50 hour inspection.
(Time permitted to comple
inspection is
ten flying
hours}.
No airplane will
go longer than one
month without a
25 hour inspection
irrespective of
flying time.
Purpose
Check of airplane to
determine that the
following are functioning prop~rly:
Instruments, ~ontrols,
auxiliary power plant.
Check cowling and see
that fuel and oil caps
are secured.
Starting and warming
up of engine. Plane
ready for flight, and
turning airplane over
to the Pilot.
To determine the general condition of the
airplane and engine.
To detect aggravated
conditions, maladjustments, breaks, etc.
Also includes ".PRE-FLIGB1'.!
Designed to be sufficiently thorough
and searching. To
allow the detection
of slight wear and
other early stages
of deterioration.
Also includes a daily
inspection.
Between the
No airplane will
Designed to be complete,
40th and 60th go longer than
thorough, and searchflying hours
three months with- ing, as f .a r as it is
after comple- out a 50 hour
within the scope of
tion of the
inspection.
the visual inspection
last previous
system.
50 hour inspec
tion. (Time
permitted to
Note - 100-200-300 Hours, etc. will
complete
be covered in inspection
ins_pection is
sheets as major items.
20 rlying hour)
�IV
SYMBOLS
The following symbols are used in the above maintenance and inspection
records: 41B for Flight Report, land lA as mentioned.
RED CROSS (x) Indicates ,.-Dangerous Condition".
This symbol grounds the airplane and is not subject to "Exceptional Release".
RED DIAGONAL(/} Indicates "Maintenance Work Necessary".
This symbol will not be used to indicate performance of routine
greasing, oiling, and cleaning required by Technical Instructions, but will be used to indicate omission of such work.
RED DASH (-) Indicates uRequired Inspection Not Made".
If a partial inspection or unfinished work leaves an assembly
incomplete (where such condition is not readily apparent, as
an unsaftied drain plug) the Red Cross (x) will be used to
insure against flight in the absence of the assigned mechanic.
BLACK LAST NAME INITIAL OF MECHANIC Indicates "Thoroughly Inspected -condition Satisfactory1t.
The initial placed over a red cross or red diagonal means that
the trouble has been corrected. A red s:ymbol will never be
placed over the initial.
If, after the initial has been entered, a condition requiring
a red symbol is discovered, the initial will be erased.
BLACK CIRCLE (0) Around Mechanic's Initial Indicates ttRoutine Maintenance
Performed". This refers to greasing, oiling, and adding water
in battery according to Technical instructions. 'T his symbol
will not be used following defects or repairs found necessary,
as such conditions are indicated by a red diagonal.
BLACK DASH(-) Indicates "Inspection Today not required".
Draw this symbol through one or more columns, when instructions
do not require inspections.
BLACK LINE (I) Drawn vertically down a column indicates "Not .t.pplicablen-.
This means that the Technical Instructions do not apply to this
airplane because of the absence of the subject part or assembly.
For instance, an airplane without night flying equipment would
require this symbol in Column 42.
Note - When a Red Diagonal(/) or a Red Dash(-) remains without an
initial, an Air Corps Officer may authorize a specific flight
by signing the ~Exceptional Releasen Column 49.
Such authorization indicates that the officer has investigated the nature
and extent of the defect and assumes full responsibility for
mechanical safety on that flight.
�Pagel
0
0
PREFLIGHT AND DAILY INSPECTIONS
Jnaert s-ial No.
After .AppUcable Model
B-17- ----------------------------------13-17D -------------------------------Orsaai..tlon and Heme Station
B-17B --------------------------------B-17E -------------------------------B-17C ________________________________ B-17F ----------------------~---
(Data)
INSPECTIONS REQUIRED
Remarks Pertalnlns
Thia form to be retained with the airplane u contlnums laatructiona
Replacements or
.AdJuatmenta
to Defects.
See T. 0. 00-20A and 00 20A-2
1
2
NOTE: An explanation of the Visual Inspection System and instructions as
to the scope and periods for accomplishment of the various periodic inspections are contained in Technical Order No. 00-20A. For more complete service and maintenance instructions refer to:
Engine T. O.
Airplane T. 0.Model
02-36GA-2
(R-1820-39)
01-20EA
Series
B-17
02-36GA-2 (R-1820-51)
0l-20EB-2
B-17B
02-35GC-2 (R-1820-65)
0l-20EC-2
B-17C
02-35GC-2 (R-1820-65)
01-20ED-2
B-17D
02-35GC-2 (R-1820-65)
0l-20EE-2
B-17E
02-35GC-2 (R-1820-65)
B-17F
Ol-20EF-2
PREFLIGHT INSPECTION
(To be performed prior to the first flight ,of the day)
BEFORE STARTING ENGINES.
10
Examine Airplane Flight Report, Form No. lA. Enter all information necessary to make it complete. If routine inspections are due, but cannot be
made, insert the proper symbols to indicate the omission of the inspections.
10
Check the quantities of fuel and oil in the tanks and enter on Form No. lA.
Note: This check and entry MUST be made prior to the first flight of the day.
10
Drain main fuel strainers and fuel tank sumps. Be sure all drain cocks and
plugs are properly resafetied.
10
Inspect landing gear for damage and obvious defeets. Check for proper tire
and shock strut inflation.
10
Make sure ignition switches are "OFF" and then inspect propeller blades for
nicks. scratches, looseness, etc.
10
10
Remove the airspeed tube protection cover. Check tube openings for freedom from obstructions. Test heating unit.
Inspect de-icer shoes for punctures, loose patches or other obvious defects
and for freedom from oil.
See that wheel chocks are in proper position.
'inspect wings, ailerons, fuselage, stabilizers, elevators and rudder for damage
or obvious defects.
10
See that cowling, inspection doors and covers are properly secured.
10
Inspect for presence of flare gun and
cartridges.
10
Check oxygen equipment for condition, completeness, sufficient pressure, and
proper functioning. For detailed service and maintenance inspections refer
to T. 0. 03-50-1.
10
Inspect CO 2 extinguishers for security of mounting and proper safetying of
actuating valve. NOTE: Once release handle is tripped complete emptying
cannot be prevented.
10
Check for proper level of fluid in heating system. Fill if necessary.
10
Note:
Uso only approved fluid in glycol
system.
3
4
�Page 2
PREFLIGHT AND DAILY INSPECTIONS
1
2
10
Check fluid level in,Hydraulic fluid r•eservoir and Propeller Anti-icer reservoir.
Fill, if necessary,j with fluid specified in the Airplane Handbook.
10
Clean all cabins and compartments (including windows). All articles which
could foul or jam controls will be properly attached, stowed or removed.
10
10
Set Altimeter to station altitude, or as directed by pilot.
10
Set Rate of Climb Indicator to ZERO, tap instrument to insure that hand is
properly, set.
10
Airspeed Indicator-See that pointer indicates zero, or value of wind velocity
.component, in direction of aircraft beading.
10
10
Check instrument panels for proper movement.
10
Check ALL INSTRUMENTS for proper pointer position and loose or broken
lenses. Clean lenses with a soft cloth being careful to not disturb setting
of "Limit-marked" lenses.
Check the lighting of all instrument, cabin, trouble, landing, passing, running, and position lamps. Replace :iefective lamps or fuses found.
Check operation of warning signals. Check operation of bomber's pilot calL
10
10
10
Check flight controls for freedom and range of operation.
10
Fill water bottles and check for an adequate supply of paper cups.
10
If an over-water flight .is contemplated see that life raft is in place.
Check for presence of hand starter crank.
DURING ENGINE WARM-UP.
Note: Before starting the engines pull propellers through several revolutions by hand to clear the combustion chambers.
CAUTION! (T. 0. 02-1-32)-Warm-up test periods should be as brief as
possible to prevent excessive wear on moving parts. Read T, 0. 02-1-29,
"Ground Operation of Aircraft Engines".
Caution! Do not operate landing gear valves or mechanical handles!
To prevent possible backfires causing damage to air intake system the carbureto.r air intake valve will be in full cold position when starting engines.
Check hydraulic system gage to see that at least l,Ot) lbs. of pressure exists
in system before starting engines.
10
Check engine instruments for functioning and proper reading.s--consistent
with the stage of engine warm-up.
10
Test ignition system as follows: With the engine not excessively hot and
operating at approximately 1/3 open throttle, turn the ignition switches
momentaril;v to the "OFF" position. If the engine does not cease firing entirely, stop the engine by turning off the fuel supply. Check for defective
"ground" connections.
WARNING! DO NOT TOUCH THE PROPELLER UNTIL THE ENGINE
HAS BECOME COOL AND THE DEFECT LOCATED AND CORRECTED,
AS THE ENGINE MAY "KICK OVER" OR START.
10
Check that fuel quantity gages register correct
amount of fuel in tanks. See T. 0. 03-10-16.
3
4
�Page 3
PREFLIGHT AND DAILY .INSPECTIONS
1
10
I
3
2
I
Check ·functioning of manifold.pressure gages.
to left.
Needle should move freely
T. 0. 06-70-1.
10
Check vacuum (4"). Check operation of vacuum pumps with selector.
10
Check operation of supe:::cha:rger regulators individually. Determine that
turbine wheels are rotating and check operation of waste gates .
. 10
Check that De-icing equipment and Anti-icing system :function properly.
Note: The Anti-icer system .should be operated daily to prevent congealing
of fluid and clogging of system.
10
10
intercooler control
10
Check operation of
10
10
Check engine primers for leakage in the "OFF" position.
24
Check operation of heating system in accordance with Airplane liandbook.
Check all steam fittin6ts, particularly at boilers, for leaks. Tighten, if necessary, at conclusion of engine run, while engine is still hot.
SPECIAL-10 Houra. Cuno Oil Filters-Check the turning mechanism of autom,tically operated oil filters for proper
operation by installing the manual turning nut, markini its position and
noting that it has moved after idling the engine for approximately 6 minutes.
Non-movement of the nut denotes defective unit and it should be replaced.
T. 0. 02-1-24.
Do not feather or unfeather more than one propeller at a time.
AUXILIARY EQUIPMENT
(The following inspections are to be accomplished when missions are
scheduled).
11
BOMBINGBomb Racks-Inspect for dirt and oil.
Racks _must b& kept d_eau and all
centact surfaces nnlished and nee. from bun-1'.
saf"eties, and general condition.
Inspect for secunty,
Check for presence of forked rod for emergency bomb release.
WARNING: The airplane will not be flown with bomb racks removed as
they form part of the primary airplane structure.
Check bomb bay door indicator.
CAUTION: When airplane is on the ground, make certain all personnel and
obstructions are clear of the bomb bay doors before door control is operated.
T. 0. 01-1-36.
12
GUNNERYMachine guns: Check forHeadspace
Mounts-security of attachment & free movement.
Feed boxes & ejection chutes--proper aligm 1t.
13
TOW TARGET-When a windlass is employed, visual and physical check
will be made to determine proper lubrication of windlass and functioning of
brake, clutch and winding mechanism. (T. 0. 11-40-4). Determine that jnstructions to windlass operators reference correct procedure in cases of malfunctioning are properly posted.
15
COMMUNICATION-Make visual ins_pection of all installed radio equipment for general condition.
(Tests of
4
�Page 4
PREFLIGHT AND DAILY INSPECTIONS
1
2
radio compasses will be conducted at a distance from hangars.)
Inspect fixed antenna system
tor conc,it1on ana see tnn mres ar-e t"aut. crean dirt and carbon from insu-.
lators. Check trailin~ antenna reel for proper operation. T. O. 08-5-2.
Check column 15, Form 41 with the Form lA to see that they check.
Check for presence of "Radio Data", T. O. 08-15-2.
NOTE: Installed radio transmitters will not be operated (dynamotor running), if any point of the antenna system is closer than one foot to any
object other than the airplane itself (T. 0. 08-5-2). Do not use pliers on any
part of antenna wires.
16
PHOTOGRAPHICNOTE: The preflight inspection is a check of the camera mount supports,
camera ports, etc., prior to the first flight of the day, and is designed to ascertain that the camera and its accessories can be readily mounted and satisfactorily used in the airplane. The inspections listed will be considered to
be the minimum required.
Clean the floor and the inside and outside surfaces of windows below camera
position.
Inspect camera mount supports for ease of adjustment, cleanliness and that
locking pins engage properly.
See that the camera door and viewfinder opening will open and close properly.
Clean the holes and slots in the viewfinder mounting ring.
Check the camera signal and power circuits.
Check the interphone station at camera position.
Check oxygen supply for camerman.
AFTER FLIGHT
30
At completion of flights involving the use of oxygen, mouth pieces (if used)
will be sterilized. Valves on oxygen cylinders will be turned off immediately.
Check contents of cylinders as indicated by pressure. (T. 0.'s 03-50-1 and
03-50A-1).
After every flight the static electricity in the de-icing boots should be discharged by wiping the entire surface of the boots with a grounded wire brush
or a similar suitable conductor. The airplane will not be refueled prior to this
operation.
19
All fuel and oil tanks will be serviced to the normal supply and quantities
entered on Form No. lA. at completion of day's ftying. Make visual inspection
of airplane while servicing.
19
At end of day's flying clean propellers, inspect, and coat with clean lubricair
ing oil. (T. 0. 03-20CC-2).
19
See that airspeed head protection cover is installed.
19
Sufficient cowling will be removed in order to cheek for fuel and oil leaks
within the engine nacelles, and for f allures of wires, lines, connections, attachments of exhaust pipes and collectors, etc.
30
Heating systems using water will be drained if airplane is to remain idle
and subjected to freezing weather!
30
Cheek racks for released flares.
3.
�Page 5
PREFLIGHT AND DAILY INSPECTIONS
2
1
12
13
DAILY
(To be performed at any time during the day)
NOTE: The inspections listed are grouped in sections for the convenience
of the personnel concerned.
SECTION 1-ENGINES AND PROPELLERS
19
Propellers and accessories--Check governors for oil leaks around bases and
heads and controls for lost motion. Inspect propellers for bent or damaged
blades, nicks, cracks, oil leakage, or other defects.
(T. 0. 03-20CC-2)
WARNING: The ignition is grounded through a plug on forward face of
each firewall. Remov~l of this plug leaves ignition on, propeller will not be
, pulled through when ignition plug is out.
REMOVE ENGINE COWLING.
EXCEPT RING COWLING.
19
Inspect engine ring cowling for security of attachment. Cowling must not
be excessively tight when engine is cold.
19
Inspect exposed portions of engine mount and mounting brackets for general
condition and security of attachment.
19
See that cowling is not rubbing cooling fins. Check for broken or damaged
baffles.
19
Check exhaust manifolds for general condition and security of attachment,
missing bolts or nuts, broken lugs, etc.
19
19
Check intake pipes for s~urity of attachment and leaking gaskets.
1.9
Inspect for evidence of engines throwing oil.
Inspect engine control assemblies for proper functioning, operating range,
tightness, safetying, and general condition:
Oft cooler shutter controL
Throttle and mixture controls.
Propeller controls.
Emergency hand pump control.
Supercharger controls.
Intercooler temperature control
19
TURBO SUPERCHARGERS-Check entire installation for security of
mounting and evidence of failure, turbine buckets for cracks and bucket
wheel for looseness. Inspect Supercharger oil supply system for leaks.
19
Inspect oil, fuel and battery vent and overflow lines for security of anchorage,
clogging, breaks or kinks and to see that lines extend below cowling.
NOTES: Not more than two men should stand on engine servicing platform
at one time.
Care must be exercised not to wash off rust preventive coating from control
cables.
SECTION 2-FUEL AND OIL SYSTEMS
19
19
Drain main fuel strainers and fuel tank sumps and resafety.
With fuel "On" and pressure built up, inspect carburetor and fuel line connections for leakage, particularly at drain plugs, passage plugs and parting
surface of body castings.
19
Check security of mounting of carburetor beater and scoops. Check carburetor for security of mounting and proper safetying.
19
Inspect carburetor air cleaner for contamination. If there is evidence of
dirt collecting, remove the unit and wash in gasoline. Allow it to dry
thoroughly and immerse in oil, Spec. AN-VV-0-446, grade 1120. Allow the
unit to drain for 2 hours, if possible, before reinstalling.- T. 0. 01-1-23.
3
4
�Page 6
Q
PREFLIGHT AND DAILY INSPECTIONS
1
2
19
Self Sealing Fuel Tanks: Visually inspect the structure surrounding the
cells, and all fittings attached to the cells which are visible through qui.ck
opening access doors, for evidence of leaks.
19
If bomb bay tanks are installed, check safety wires.
19
Check all oil system drain plui:s and drain cocks for leakage and proper
safetying.
19
Inspect o.il coolers for security of mounting and evidence of clogging. Inspect
for proper blanketing according to weather conditions and existing orders.
(T. 0. 06-10-1).
SPECIAL-12 Hours.
23
Check fuel systems which HAVE NOT been treated for use of Aromatic
fuels for deterioration and defective parts. T. 0. 01-1-118.
SPECIAL-EVERY 30 DAYS.
23
1. Check fuel systems which HA VE been treated for use of Aromatic fuels
for correct and discernible identification marking. T. 0. 01-1-118.
2. Replace diaphragms and seals in fuel pumps and injection carburetors
of fuel systems which HAVE NOT been treated for use of Aromatic fuels.
T. 0. 01-1-118.
SECTION 3-IGNITION AND ELECTRICAL
19
Inspect generators, starters, switches, coils, solenoids and magnetos for
cracked housing or flanges, security of mounting, tightness of housing bolts,
safetying, etc.
19
Inspect parting surfaces of starters for evidence of oil in starter gear cases
or around fly wheel.
19
Check booster coils for operation.
19
Replace engine section cowling and check for security of attachment.
46
SPECIAL-WEEKLY. Take hydrometer readings on batteries, if any cell
is too hi2'h or too low. turn battery in for check. Add distilled water as necessary, never add electrolyte or acid. Inspect battery leads, and check to
see that vents are open. T. O. 03-5B-1.
SECTION 4-LANDING GEAR AND HYDRAULIC SYSTEM
30
Make visual inspection of landini: gear for:
General condition of struts, braces and fittings.
Shock struts for proper inflation and evidence of leakage.
Wheels for bent or distorted rims, security of retaining bolts and nuts.
Tires for proper inflation, general condition, cuts, pulling away from
rims and evidence of interference or chafing against other parts.
Condition of tail wheel shear bolt.
Proper safetying of all units.
30
Check for evidence of fluid leaks in Hydraulic system.
SECTION 5-INSTRUMENTS
30
30
30
39
Check instrument panels for proper movement.
Check the lighting of all instrument, cabin, trouble, landing, passing, running, and position lamps, and replace any defective lamps found. Check
operation of warning bell at all locations. Check operation of bomber's pilot
call.
Check compasses for bubbles and discoloration of liquid.
SPECIAL-10 Hours.
Tum the handle of Cuno hydraulic filter one complete revolution in each
direction. (Turn, also, at least once during the first hour of operation after
hydraulic system overhaul or fluid change). T. 0. 08-30-2.
3
4
�Page 7
PREFLIGHT AND DAILY INSPECTIONS
1
2
SECTION &-MISCELLANEOUS
30
Inspect wings, fuselage, vertical and horizontal stabilizers for gener::! l condition; distortion, pulled rivets or other evidences of failure; security of
attachment, etc.
30
Inspect flight control surfaces (flaps, ailerons, rudder and elevators) for
general condition.
30
30
30
Inspect De-icer shoes for bruises, punctures, loose patches, etc.
Check condition of static ground, T. 0. 01-1-5.
Fire-extinguishers, hand, Type A-2, check for contents, security of mountil)g
bracket, nozzle opening unobstructed, tag intact, secure in bracket yet easily
removed. Replace if defective (T. 0. 03-45-1).
30
Check CO 2 bottles of pneumatic life raft and engine fire extinguisher to see
that safety discs have not been ruptured. T. 0. 16-20-2. The CO 2 release
cable must be disconnected from the life .raft door latch before pulling the
release handle.
30
Clean all cabins and compartments (including windows). All articles which
could foul or jam controls will be properly attached, stowed or removed.
30
Check flight control mechanism for fre.edom of operation, Cheek that control cables are protected with rust preventive compound.
30
30
30
30
See that "Pilot's Check List" is accessible to pilot.
Lubricate foot pedal and brake rod controls with oil.
Clean toilet. Fill receptacle with one quart of disinfectant solution.
Check fluid level in anti-icer reservoirs. Fill, if necessary, with fluid, Spec.
3686.
30
Heating and Ventilating System-Inspect entire system for leaks and general
condition of units, lines and fittings.
30
SAFETY BELTS: Inspect fabric and leather parts for cuts or frayi"Q.g,
latching devices for condition and operation; fittings and attachment parts
for condition and security of fastening. Check for date of last weight test.
T. O. 03-1-2.
19
3
4
�Fage 8
insert Serial No.
After Applicable Model
25-HOUR INSPECTIONS
(Perform preflight and daily inspections as usual in addition to thb Inspection)
B-17 ·····-----------------·-----------B-17D -·--·-----·---------------·----·
· Organization and Home Station
B-17B ·------ -·-----------------------B-1 7£ ---- --- -----------------·--··--·
···-··--·--····-····-----·····
(Date)
B-17C _____ ___ _ ---------------------B-17F ----------------------
INSPECTIONS REQUIRED
Remarks Pertaining
to Defects,
Replacements or
Adjustments
Accomplish one copy of this form at each 25-hour inspection.
Turn in completed forms to Organization Engineering Officer.
See T. 0. 00-20A and 00-20A-2
3
1
2
29
POWER PLANT-GENERAL: With engine ring cowls left on, make a
rigid inspection of each entire engine and mountings. Oheck engine ring
cowl supports and engine mounting lugs for tightness of bolts and condition
of rubber bushings.
COOLING SYSTEM: Inspect engine cowl flaps and magneto cooling tubes
for cracks or other damage, proper alignment and security of mounting.
Check cylinders for damaged or broken fins. Lubricate cowl flap and the
flap control system with oil.
SECTION !-ENGINES AND PROPELLERS.
25
20
ENGINE CONTROLS-1. Inspect entire control installation from levers in pilot's compartment
through all rods and cables, linkage, support brackets and pulleys. Inspect
for full and free movement, lost motion, bent rods, frayed cables, loose,
broken or misaligned pulleys, loose or missing bolts, nuts, screws, cotter pins,
etc. See that linkage is properly adjusted. Controls should operate with
uniform tension throughout their full range. See that all adjustment or
position locking devices function properly and that all levers are adjusted
to prevent creeping. See that throttle stops are adjusted to prevent creeping. Clean and lubricate all moving connections and bellcranks.
The above applies to throttle, mixture, carburetor heater, emergency hand
pump, supercharger, intercooler temperature, propeller and oil cooler controls.
NOTE: On newly installed engines perform 25 hour after engine change
inspection, if due.
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Organization and Station)
SECTION 2-FUEL AND OIL SYSTEMS.
23
FUEL SYSTEM1. Fuel Pumps. Clear vent opening in relief valve cover plug by inserting
a drill or a wire. Che{!k u.umps for §_ecurity of mounting, leaks, and proper
operation. vhe ck oaJ. an ce J. ine •
2. CARBURETOR: Lubricate throttle shaft bushings using oil, machine
gun, Spec. 2-27. (T. O. 03-lOBA-2). Inspect parting surfaces between body
castings, test screws with screwdriver for tightness. Remove <:_arburetor air
maze-wash in gasoline and allow it to dry thoroughly. Immerse in lubricating oil and allow it to drain for 2 hours before reinstalling. T. 0. 01-1-29.
3. FUEL STRAINERS: Remove and clean fuel strainer screens; inspect
for breaks and tears. Clean strainer bodies. Replace strainer screens, plu_gs
and drain valves and resafety.
4.
BOOST PUMPS: Inspect for leaks and operation.
5. FUEL LINES: With fuel booster pumps on, inspect all fuel lines for
leaks (particularly at eonnections and at sharp bends), cracks, security of
line anchorage, and wear due to loose clamp, vibration or chafing. Inspect
condition of hose connections and tightness of hose clamps.
35
EUEL TANKS: Check tanks for evidence of leaks; check safetying of latches
of releases for bomb bay tanks.
24
OIL SYSTEM1. Remove and clean Cuno filter cartridge. Check cartridge rotation.
Check that all cleaner blades are straight and flat. Check that all discs are
flat, evenly spaced, and free from burrs or nicks. T. 0. 02-1-24.
4
�Page 9
0
25-HOUR INSPECTIONS
1
3
2
2. OIL LINES: Inspect for leaks (particularly at connections and passage
through firewall or other structure), security of attachment, dents, cracks,
chafing, etc. Hose connections and hose clamps for general condition and
for proper location of clamps.
3. OIL SCREENS: Remove and clean whenever oil is changed.
I hereby certify that I have performed-supervised-the above inspections.
(Name. Grade-----······
and Duty)
(Organization and Station)
SECTION 3-IGNITION AND ELECTRICAL
22
46
SPARK PLUGS:
1. Check and reset gap to .012" ( +.002"; - .001"). If gap setting equipm~nt
is not available, replace with new or reconditioned plugs. T. 0. 0l-20E-82.
Check elbow terminals and shielding nuts of shielded spark plugs installatiQJlS
for security. When tightening the elbow assembly of shielded plugs, the
barrel must not be loosened. Care must be exercised to see that the barrel
is not rotated with respect to the shell since this will change the gap setting.
(T. 0. 03-5E-1).
2. Inspect landing gear limit switches for security of connections and ! or
proper operation through access doors.
3. Remove cover from switch panel and inspect for security of connections,
freedom of operation, and general condition. Remove all accumulated dust
and foreign material with air blast.
4. Inspect all other electrical switches in airplane for security of connections,
correct operation and for general condition. Where practicable, inspect the
condition of switch contacts.
BATTERY: Inspect the felt pad in the battery vent sump for proper condition. Saturate, if necessary, with solution of sodium bicarbonate and water.
(T. 0. 01-1-20) T. 0. 03-5B-1.
I hereby certify that.I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Organization and Station)
SECTION 4-LANDING GEAR AND HYDRAULIC SYSTEM.
36-37
38
39
LANDING GEAR AND TAIL GEAR1. Inspect struts, braces, drag links, retracting mechanism, and fittings,
for cracks, bends, security and condition of attachment fittings, elongated
bolt holes. Check for loose, missing or unsafetied bolts, nuts or cotter pins.
Inspect Landing Gear Drag Strut on B-17O, D & E airplanes in accordance
with Technical Radiogram 0l-20E-80 pending compliance with T. 0. 0l-20E-86.
2. Lubricate landing gear.
3. Check shock strut for fluid level-refill, if necessary. See the airplane
handbook and T. 0. 03-25E-1.
4. Check for proper operation of swivel mechanism, and tail gear centering
lock. Locking plunger should "BOTTOM" in slot when tail gear is in trailing
position.
WHEELS AND BRAKES: With parking brake set inspect entire hookup
from resen·oir to wheel cylinders for leaks, condition of attaching clips and
flexible connection~. Jm;pect brakes for entrapped air (soft spongy feel to
brake action) arnl for leakage at brake cylinder sleeve. Cheek clearance between brake lining and brake drum. Brakes should hold airplane at full
throttle.
HYDRAULIC SYSTEM1. HYDRAULIC LINES: Inspect all lines and connections for leaks, de~ts,
kinks, or cracks, security of anchorage, wear due to chafing or vibration, e,te.
Inspect for deterioration of flexible connections.
2. VALVES: Inspect all valves for general condition, proper operation,
nnd evidence of leakage.
3. PUMPS: Check motor driven and hand operated hydraulic pump for
condition and functioning. Check pressure regulator for leakage.
4
�Page 10
25-HOUR INSPECTIONS
1
3
2
4. ACCUMULATOR: Inspect for indications of leakage. Check that accumulator will operate hydraulic system. To service accumulator see airplane handbook.
5. FLUID RESERVOIR: Check fluid level. Fill with oil, Spec. 3580 to
proper level. (T. 0. 06-1-2). Bleeding of air is accomplished by several
slow applications and complete releases of pressure to the brakes. This procedure bleeds entire system.
I hereby certify that I have performed-supervised-the above inspections.
-----·---- •····
(Name, Grade and Dut:,)
---..,......----•··•···
( Ora:anization and Station)
-21
34
40
33
32
SECTION 6-MISCELLANEOUS.
FIXED SURFACES: Make inspection of wings, horizontal and vertical
stabilizers and fairings for cracks, loose rivets, loose screws and general
condition, corrosion, etc. Check landing lamp reflectors f Qr polish.
FUSELAGE: Inspect for general condition, corrosion, pulled rivets, rupture
or distortion indicating failure, damage at cabin entrance, etc.
MOVABLE SURF ACES: Inspect ailerons, elevators, rudder, flaps and tabs
for free and full movement, warping, broken ribs, or ribs loose on spars, condition of covering, condition of hinges and security of attachment. Inspect
horns and hinges for bends and breaks, security of attachment, worn or loose
hinge pins, and for proper safetying.
FLIGHT CONTROL MECHANISM1. At first 25 (and subsequent 100-hour inspections) check tension of control cables. If adjustments are necessary see airplane handbook and T. 0.
01-1-9 for details.
2. Lubricate flight and flap control mechanism in accordance with airplane
handbook.
3. Make inspection of flight control mechanisms as follows:
a. Inspect cables for frayed wires. (Not more than 6 broken wires per
inch).
b. Inspect ·f or broken, loose or misaligned pulleys.
c. Inspect rods for freedom of movement and for condition of bearings
and sliding surfaces.
d. Inspect guides for general condition, proper alignment and security
of mounting.
e. Inspect brackets for security of attachment, cracks or other defects.
f. Inspect rudder pedal assembly for proper functioning of the parts;
lost motion or binding. Check for proper setting of the rudder pedals
and the rudder when in neutral position and check that rudder doesn't
interfere with the elevators when in extreme positions.
g. Inspect wheel control for condition and proper functioning of the
parts. Check for lost motion or binding in the wheel assembly.
h. Check tab mechanism for proper functioning.
i. Inspect flaps for proper condition and check that the cockpit indicator
shows corr~ct position of the flaps.
Refer to Airplane Hand book for adjustment instructions.
32
43
AIRCRAFT GENERAL-!. DE-ICING EQUIPMENT: Check de-icing shoe attaching screws for
tightness. Check feed lines in both wing and tail for security and general
condition. (T. 0. 03-35B-1.)
2. ANTI-ICING EQUIPMENT: Inspect for security of attachment of
lines leading from tank to propeller hubs. Check for condition of connections.
...
4
�Page 11
0
25-BOUR INSPECTIONS
1
42
31
3
2
3. HEATING AND VENTILATING SYSTEM: Inspect for leaks and cQndition of units' lines and fittings, condition and operation of ventilators. Inspect defroster tubes for leaks and for proper operation.
4. Inspect first-aid kits to determine items required for replacement. Required items will be obtained by requisition from the local Medical Department, T. 0. 01-1-117.
NIGHT FLYING EQUIPMENT: Remove flares and inspect for dents, wear
of carrying hooks, corrosion, date of expiration ( date of removal from fibre
container should be on flare); damage to body carrying illuminant; condition
of operating and attaching mechanism. T. 0. 11-15-1).
COCKPITS AND CABINS-1. SEATS: Inspect for security of attachment (including supports and
brackets), condition and functioning of adjusting mechanism, breaks or
cracks in the seats, which could foul parachute or clothing. Oil seat adjustments.
2. WINDSHIELDS, WINDOWS, TURRETS AND DOORS: Inspect for
condition of frame and security of attachment. Breaks or cracks in glass or
transparent sheet. Condition and operation of mechanism on sliding windo-yvs
and doors. Inspect for cleanliness of all windshilds and windows.
3. VENTILATORS: Check for condition and proper operation.
4. EMERGENCY EXITS: Check cabin door and emergency exits for condition and proper operation.
5. SAFETY BELTS: Inspect fabric and leather parts for cuts or fraying,
latching devices for condition and operation; fittings and attachment par:ts
for condition and security of fastening. Check for date, of last weight te·s t.
All belts to be tested semi-annually except type B-11, which are to be tested
annually (T. 0. 03-1-2).
I hereby certify that I have performed-supervised-the above inspections.
(Nc\llle, Grade and Duty)
(Organization and Station)
SECTION 8-AUXILIARY EQUIPMENT.
11
BOMBING1. Grease bomb door operating units, bomb release slide and bomb control
levers in accordance with Airplane Handbook.
2. BOMB RACKS: Make detailed inspection of structure, installation fittings, releasing and arming mechanisms, and electric circuits for evidence
of wear or failure.
3. Clean racks with kerosene, Spec. VV-K-211.
4. BOMB RACK CONTROLS: Inspect all connecting members, mechanical
and electrical, between control units and rack assemblies; check control J;!Ositions for proper relation tliroughout the system. Determine correct operation with respect to both functioning and proper sequence of operation.
5. Thoroughly clean entire control system.
12
13
(Organization and Station)
4
�Page 12:
50-HOUR INSPECTIONS
Insert Serial No.
After ApplicaJ,le Mo4el
(ZS-hour inspection• inclucled ancl marked •-Perform preOlfht and
clally Inspection• as usual in acldltion to thia inapectloa
B-17 ··································B-17D ············-·--·-··---·-···---Orpnlation aad Home Station
B-17B ................................B-17E ................................
B-17C ································:n-17f ......................
(Date)
INSPECTIONS REQUIRED
Accomplish one copy of this form at -ch SO-hour inspection.
in completed forms to Or•anization En•ineerln• Officer.
Remarks Pertainin•
to Defects,
Turn
Replacemeata or
Adjustments
See T. O. 00-20A and 00-20A-Z
2
1
REMOVE ALL ENGINE SECTION COWLING, INCLUDING ENGINE
RING COWL, AND OPEN ALL INSPECTION DOORS AND COVERS
SECTION I-ENGINE AND PROPELLER
28
PROPELLERS AND ACCESSORIES!. Using magnifying glass, carefully examine exterior of all parts of propellers for cracks, nicks, bends, and similar defects. Check for deterioration
of markings and for proper safetying. (T. 0. 03-20CC-2).
Propeller Governors-Check governors for oil leakage and for security
of mounting; check control system for security of attachment, freedom of
movement, proper safetying, loose or worn bearings. Check governor assembly for free movement of drive. (T. 0. 03-20CA-2).
2.
3.
Check condition and operation of cockpit propeller controls.
4. Check propeller anti-icing pump and motor for security of mounting and
for leakage in system.
29
POWER PLANT GENERAL!. Inspect CYLINDERS for cracks broken or damaged fins; BAFFLES for
cracks, loose rivets and security of mounting.
Check all clamps, bondings, tapeing and safetying of all lines, and all rods
within the engine section of nacelle.
2.
Inspect engine MOUNTS for cracks (particulady at welds), tightness of
mounting, security of engine to mount, mount to nacelle.
3.
4.
27
Lubricate starter handcrank extension-support bearings with oil.
MANIFOLDS AND SUPERCHARGERS: Inspect intake and exhaust sy,stem for damaged manifolds, loose stacks and retaining lugs, broken or loose
studs and bolts, blown gaskets. Lightly tap exhaust stacks to loosen any
scale formation or brush out with wire brush.
1. Turbo superchargers-Inspect lines for condition and tightness. Test
lines for leaks (Section 5, T. 0. 03-l0DA-2). Remove any accumulation of
carbon from system. Check exhaust manifold and nozzle box for cracks.
Draw off small amount of oil from supply tank, if oil contains abrasive particles, drain, flush and refill with fresh oil.
Supercharger regulators-Check for security of mounting, proper attachment of lines and excessive leakage. Leakage of over one drop per
minute at 50 lbs. pressure and normal temperature will be considered excessi~e and unit will be removed for repairs or gasket replacement as necessary.
T. 0. 03-lOD-2.
2.
25
*COOLING SYSTEM: Inspect engine cowl flaps and magneto cooling tubes
for cracks or other damage, proper alignment and security of mountil)g.
Check cylinders for damaged or broken fins. Lubricate cowl flap, and the
flap and scoop control system.
20
ENGINE CONTROLS*!. Inspect entire control installation from levers in pilot's compartment
through all rods and cables, linkage, support brackets and pulleys. Inspect
for full and free movement, lost motion, bent rods, frayed cables, loose,
broken or misaligned pulleys, loose or missing bolts, nuts, screws, cotter
pins, etc. See that linkage is properly adjusted. Controls should operate
with uniform tension throughout their full range. See that all adjustment or
position locking devices are adjusted to prevent creeping. See that throttle
stops are adjusted properly to prevent creeping. Clean and lubricate all
moving connections and bellcranks.
The above applies to throttle, mixture, carburetor heater, emergency hand
pump, supercharger, intercooler temperature, propeller, and oil cooler controls.
3
4
'
··
�Page 13
50-HOUR INSPECTIONS
3·
2
2. All control cableJ, will be cleaned where they pass over pulleys or through
fairleads and coverec:l with compound, rust preventive, heavy, Spec. 2-82.
I hereby certify that I have performed-supervised-the above inspections.
( Name, Grade and Duty)
(Ors-lzatloa and Station)
SECTION 2-FUEL AND OIL SYSTEMS.
23
FUEL SYSTEM•1. FUEL PUMPS: Clear vent opening in relief valve cover plug by inserting a drill or a wire. Check pumps for security of mounting, leaks, and
prope.i operation.
2. CARBURETOR: Lubricate throttle shaft bushings using oil, machine
gun, Spec. 2-27. (T. 0. 03-l0BA-2). Inspect parting surfaces between body
castings, test lfcrews with screwdriver for tightness. Remove carburetor air
maze-wash in gasoline and allow it to dry thoroughly. Immerse in lubricating oil and allow it to drain for 2 hours before reinstalling. T. 0. 01-1-29.
Drain regulator unit, air chamber, fuel chambers and fuel control unit through
plugs in bottom.
•a. FUEL STRAINERS. Remove and clean all fuel strain·e r screens. lns~t
for b1-eaks and tears. Clean strainer bodies. Replace screens, plugs and
drain valves and resafety.
*4.
BOOST PUMPS :Inspect for leaks and operatic n.
*5. FUEL LINES: With fuel "On" and pressure built up, inspect all fuel
lines for leaks (particularly at connections and sharp bends), cracks, security
of line anchoraire; wear due to loose clamps, vibration or chafing. Inspect
hose connections for condition, hose connections and hose clamps for tigh~
ness.
7. Inspect all fuel overflow and drain lines for security of mounting, kinks,
breaks or stoppages.
8.
35
35
24
Inspect by-pass valves for leaks and proper operation.
Check capacity of self-sealing fuel tanks in accordance with T. 0. 03-1-15.
FUEL TANKS: Inspect for security of mounting, indications of leakare,
condition and position of padding, proper tension. of supporting straps and
proper anchorage of fuel lines leading from tanks. Check condition and
proper safetying of bomb bay tank release mechanism. The fuel tank access
doors are primary structural members and care must be taken that they are
re-installed properly. Support outboard nacelle on jack before removing
doors. The bomb bay tanks are releasable by either normal or emergency
bomb controls.
OIL SYSTEM•1. Remove and clean Cuno filter cartridge. Check cartridge rotation.
Check that all cleaner blades are straight and flat. Check that all discs are
flat, evenly spaced, and free from burrs or nicks.
•2. OIL LINES: Inspect for leaks (particularly at connections and passage through firewall or other structure), security of attachment, dents,
cracks, chafing, etc. Hose connections and hose clamps for general condition
and for proper location of clamps.
3. Inspect oil system vent lines for clogging, kinks, and for security of
anchorage.
4. OIL SCREENS: Remove and clean all removable oil screens and strainers. Inspect strainers for breaks or tears.
4
�0
Page 14
50-HOUR INSPECTIONS
2
1
3
4
5. OIL COOLERS: Inspect for security of mounting, general condition and
for evidence of clogging.
OIL TANKS: Inspect for security of mounting, signs of leakage, condition and location of padding, proper tension of supporting straps and for
proper anchorage of lines leading from tanks.
6.
8. See T. 0. 02-1-22 for pre-oiling of engines (before starting engines after
oil change).
Inspect the oil dilution control linkage to insure that the linkage does not
bind at any point and that it is adjusted so that the dilution valve will close
completely. Disconnect the dilution lines from the oil line, maintain fuel
pressure with hand pump, operate dilution switches. When switches are
open, there should be no leakage through solenoid valves. T. 0. 08-15-3.
9.
I hereby certify that I have performed-supervised-the abov-e ins~tion,.
'
( Name, Cracle aacl Duty)
(Orsanizatioa and Station)
SECTION 3--IGNITION AND ELECTRICAL
22
SPARK PLUGS:
1.
Check and reset gap to .012" (+.002"; - .001"). If gap setting equipment
is not available, replace with new or reconditioned plugs. T. O. 01-20E-82.
Check elbow terminals and shielding nuts of shielded spark plugs installations
for security. When tightening the elbow assembly of shielded plugs, the
barrel must not be loosened. Care must be exercised to see that the barrel
is not rotated with respect to the shell since this will change the gap setting.
(T. 0. 03-5E-1).
2. BOOSTER COIL: Inspect for security of mounting. T. 0. 03-5-9.
3. GENERATORS: Remove generator brush bands and check brushes for
wearing, sticking, and for loose connections. Check Commutators for cleanliness and pitting. Check for presence of engine. oil in generators.
4. GENERATOR CONTROL PANEL: Inspect for security of mounting,
excessive arcing, cleanliness, condition of contact points, proper safetying,
etc. Inspect terminals, cables and connections for condition and security of
attachment. Check condition of vibration absorption mounts. Check voltage
regulator element for proper volt setting with no lead, T. 0. 03-5AB-2.
5. IGNITION SHIELDING: Jnspect for proper anchorage and security of
union nuts.
6. MAGNETOS: Type SF-9L-l, read instructions for inspectioq_and maintenance in Section 5, of Technical Order 03-5DA-2.
7. SOLENOID SWITCHES: Check for security of mounting, and of all
electrical connections. T. 0. 03-5C-2.
STARTERS· AND STARTER MOTORS: Type C-21, the window strap
on the motor will be removed and the motor inspected for loose connections
and worn or bindinJ brushes, the brush springs for tension, and the commutator for dirt and pitting. T. 0. 03-6CA-1.
9. MOTOR DRIVEN HYDRAULIC PUMPS: Remove window strap on
motor and check connections. Check for loose, binding or worn brushes.
8.
10. DE-ICER PUMPS: Remove brush and spring assemblies from motor
pump unit, and check length and condition of brushes. (This check may be
delayed, when de-icer is used infrequently). (T. O. 03-35A-1).
ELECTRICAL CONNECTIONS: Inspect all electrical connections and
leads for security of ground connections, anchorage of lines, tightness of
connections, condition of insulation~ safetying and security of Cannon type
plugs.
11.
12. Retracting motors-Check setting of clutches on retracting motors as
follows:
Bomb doors
1200 inch lbs.
Wing flaps
675 inch lbs.
250 inch lbs.
Tail wheel
800 inch lbs.
Landing gear
...
(
�Page 15
()
50-HOUR INSPECTIONS
1
3
2
Check 111otors for: c~anlines1 and for security of mounting, worn or bindi~g
brushes, loose or dlrty connections and proper safetying. Maximum permissible wear of brushes is to 3/16" from a new length of 9/3...2" repl11ce
before maximum wear limit is reached). (See T. 0. 03-5CC-1 for replacement
instructions. Check conditfon of commutator (smooth and polish with #000
sandpaper if rough), For badly scored commutator see T. 0. O3-6CC-1. Remove and check brush spring assemblies for required tension, replace if
tension is less than 38 ounees with spring compressed to 9/16" as measured
from top of metal spring retainer.
46
BATTERY: Inspect the felt pad in the battery vent sump for proper condition. Saturate, if necessary, with solution of sodium bicarbonate and
water. (T. 0. 01-1-20) T. 0. 03-5B-1.
I hereby certify that I have performed-supervised-the above inspections.
··
(Name, Gr~d• and Duty)
(Oraranization and Station)
SECTION 4-LANDING GEAR AND HYDRAULIC SYSTEM.
36-37
LANDING GEAR AND TAIL GEAR*1. Inspect struts, braces and fittings for cracks, bends, security and condition of attachment fittings, and welds, and for elongated bolt holes. Check
for loose, missing or unsaf etied bolts, nuts or cotter pins.,
•2.
Lubricate landing gear in accordance with Airplane Handbook.
3. Test functioning of landing gear retracting and lowering mechanism.
See T. 0. 19-1-18 for instructions on the use of airplane jacks before raising
the airplane. Check control and functioning of retracting mechanism; condition of torque tubes, flexible connections and couplings. Check operation
and condition of latches, limit switches, warning signals and position indicators.
4. Inspect oleo cylinders for possible interference with bolts which attach
lower collar to main strut. (Should be clearance of at least .011"). Replace
collar if interference exists.
38
6.
Inspect neoprene bumpers on stops for condition. Replace if necessary.
6.
Check fluid level of shock absorber struts as follows (T. 0. 03-26E-1):
Back off filler plug slightly and allow air to escape slowly until all I,..,. __
"fizzing" ceases. Remove filler plugs.
Fluid level should be flush with filler plug hole when strut fully collapsed
and the airplane in normal taxiing position.
Fill if necessary with Fluid, hydraulic, Spec. 3580. Check by extending
and collapsing strut several times.
........
WHEELS AND BRAKES•1. BRAKES: With parking brake set inspect entire hookup from reservoir to wheel cylinders for leaks, condition of attaching clips and flex_ile
connections. Inspect brakes for entrapped air ( soft spongy feel to brake
action), and for leakage at brake cylinder. Check clearence between brake
lining and brake drum (should be .010 inch). (T. 0. 03-25B-2. B-17B and
B-17C. Refer to T. 0. 03-25B-2 if brakes need adjustment). Brakes should
hold airplane at full throttle.
2. WHEELS: Inspect for evidence of corrosion of the 'Visible portion of
the wheel rim al}d for evidence of damage to wheel rim edges.
3. TIRES: Inspect for tread wear exposing fabric carcass of casing-replace if this defect is found. Inspect for external cuts, breaks, blisters or
other visible damage--repair if practicable.
39
HYDRAULIC SYSTEM•1. HYDRAULIC LINES: Inspect all lines and connections for leaks,
kinks, dents or cracks, security of anchorage, wear due to chafing or vibration,
etc.
*2. VALVES: Inspect all valves for general condition and for evidence of
leakage.
*3. PUMPS:
functioning.
C' ·ck hand operated hydraulic pump for condition and
*4. ACCUMULATOR: Inspect for indications of leakage. Check that
accumulator will operate hydraulic system. To service accumulator""' set
Section 3, T. 0. 0l-20EB-2 (B-17B) or T. 0. 0l-20EC-2 (B-17C), Or ·l.· • U.
Ol-20EF-2.
4
�Page 16
50-HOUR INSPECTIONS
1
3
2
*5. FLUID RESERVOIR: Check for fluid level. Fill with oil, Spec. 3680
to proper level, capacity of tank 1.94 gals. (T. 0. 06-1-2). Bleeding of air
is accomplished by several slow applications and complete releases of pressure to the brakes. This procedure bleeds entire system.
6. PUMPS, HYDRAULIC: Check tightness of attaching nuts and inlet
and discharge fittings, if leaks are indicated, test as directed in T. 0.
03-30CA-1. See T. 0. 03-30CC-3.
7. Inspect power brake control valve, adjust if necessary.
I hereby certify that I have performed-supervised-the above inspections.
(Name. Grade a1¥1 Duty)
(Orsanization and Station)
SECTION 5-INSTRUMENTS
GENERAL-Inspect all instruments for chipped or discolored luminous
markings, correct and discernible operations markings, security of mounting
and tightness of connections. Check electrical instruments for tightness of
connections and condition of insulation. Check pressure gage connections
for leaks.
21
ENGINE INSTRUMENTS-
2. Check instrument zero of Carburetor Mixture and Oil Temperature
Thermometers, adjust if necessary (T. 0. 06-40-12).
3. Thermocouple Thermometer-Check indicator as to zero position, adjust
if necessary (T. O. 05-40-3).
4. Manifold Pressure Gage-Check reading of instrument with Station Barometer. If it differs more than 0.4 inches of mercury, replace and turn in
defective instrument for bench check. (T. 0. 05-70-1).
5. Check markings of Thermometers (T. 0. 06-1-16).
6. Check marking of Engine instruments (T. 0. 05-1-17).
44
NAVIGATION INSTRUMENTS!. Magnetic Compass-Note if compass is ~ be swung. Inspect for discoloration of liquid, unbalanced card or other defects which might affect
operation. (T. 0. 06-15-2).
2. Altimeters-Set pointers at zero. Check reading of setting markers
against Station Barometer. If a difference exists, adjust. (T. 0. 06-30-10).
3. Flight Indicators-Clean screens.
4. Bank and Turn Indicators-Clean screens.
6. Rate of Climb Indicator-Check installation for loose attachment of
indicator and tank, and tubing connections in static line and from indicator
to tank for tightness. (T. 0. 05-20-26).
6. Airspeed Lines-Inspect for security of mounting and tightness of connections. Drain airspeed lines. Check airspeed head for security of mounting and for general condition. Clean holes in airspeed head with soft copper
wire. Check electrical h~ating element. (T. 0. 05-10-2).
7. Check instrument boards for defective shock mounting; bonding on
boards, lines and instruments.
I hereby certify that I have performed-supervised-the above inspections!
····
(Nam•. Grade and Duty)
(Orsanization and Station)
SECTION 6-MISCELLANEOUS.
34
FIXED SURFACES*1. Make inspection of wings, horizontal and vertical stabilizers and fairings
for cracks, loose rivets, loose screws and general condition, corrosion, etc.
Check landing lamp reflectors for polish.
.....
...
4
�Page 17
0
50-HOUR INSPECTIONS
1
2
3
4
2. Inspect flaps far condition of hinges, absence of binding and sufficient
lubrication.
3. Inspect wing and empennage attachment taper pins, tighten if necessary.
40
FUSELAGE: Inspect interior and exterior of fuselage for general condition
of skin, inspection doors, escape hatches, and windows.
33
*MOVABLE SURFACES: Inspect ailerons, elevators, rudder, flaps and
tabs for free and full movement, warping, condition of covering, condition of
hinges and security of attachment.
32
FLIGHT CONTROL MECHANISM1. All cables will be cleaned where they pass over pulleys or through fairleads and covered with compound, heavy, rust preventive, Spec. 2-82.
•2. Lubricate flight and flap control mechanisms in accordance with Airplane Handbook.
ff
*3.
Make inspection of flight control mechanisms as follows:
a. Inspect cables for frayed wires. (Not more than 6 broken wires per
inch).
b. Inspect for broken, loose or misaligned pulleys.
c. Inspect rods for :freedom of movement and for condition of bearings
and sliding surfaces.
d. Inspect guides for general condition, proper alignment and security
of mounting.
e. Inspect brackets for security of attachment, cracks or other defects.
f. Inspect rudder pedal assembly for proper functiqning of the parts;
loose motion or binding. Check for proper setting of the rudder ped,ls
and the rudder when in neutral position and check that rudder doesn't
interfere with the elevators when in extreme positions.
g. Inspect wheel control for condition and proper functioning of the
parts. Check for lost motion or binding in the wheel assembly.
h. Check tab mechanism for proper functioning.
i. Inspect flaps for proper condition and check that the cockpit indicator
shows correct position of the flaps.
Refer to Airplane Handbook for adjustment instructions.
4. Lubricate rudder and elevator locks in accordance with Airplane Handbook.
43
AIRCRAFT GENERAL-1. DE-ICING EQUIPMENT: Check de-icing boot attaching screws for
tightness. Check feed lines in both wings and tail for security and gen-eral
condition. T. 0. 03-35B-1). Lubricate windshield defroster quadrant with
fibre grease, grade 285, Spec. 3660 (B-17B).
Inspect air distributor valve as follows:
Unscrew the slotted bakelite caps on each side of the motor and remove
the brush and spring assemblies. Replace brushes if worn to a length ·
of 13/32 inches. Brushes should be a free fit without excessive side play.
(T. 0. 03-35B-4).
Drain de-icer sumps.
2. LIFE RAFTS: Remove raft from carrying case or compartment. Inspect CO 2 cylinder for proper installation, ruptured safety indicator disc and
for removal of safetying from handle. Check top-off valves in each compartment for tightness. See that all accessories are installed. Check accessories
and raft for general condition. (T. 0. 03-56A-1).
3. Lubricate starter control brackets and bandies in accordance with Airplane Handbook.
4. Remove old grease from the bomb bay door worm and nut mechanism
by washing with kerosene. Re-lubricate (sparingly) with grease, Spec. 3588.
T. 0. 0l-20E-78.
42
*NIGHT FLYING EQUIPMENT: Remove flares and inspectfor dents, wear
of carrying hooks, corrosion, date of expiration (date of removal from fibre
container should be on flare); damage to body carrying illuminant; condition
of operating and attaching mechanism. (T. 0. 11-15-1).
31
COCKPITS AND CABINS-•1. SEATS: Inspect for security of attachment (including supports and
bracket), condition and functioning of adjusting mechanism, breaks or
cracks in the seats which could foul parachute or clothing. Oil seat adjustments.
...
♦
�Page 18
50-HOUR INSPECTIONS
1
3
2
*2. WINDSHIELDS & SLIDING ENCLOSURES: Inspect for condition of
frame· and security ·of attachment. Breaks or cracks in glass or transparent
sheet. Condition and operation of mechanism on sliding parts.
•a. VENTILATORS: Check for condition and proper operation.
*4. EMERGENCY EXITS: Check cabin door and emergency exits for condition and proper operation.
*5. SAFETY BELTS: Inspect fabric and leather parts for cuts or fraying, latching devices for condition and operation, fittings and attachment
parts for condition and security of fastening. Check for date of last weight
test. All belts to be tested semi-annually except type B-11, which are to be
tested annually. (T. 0. 03-1-2).
6. Fire Extinguishers, CO 2 , remove tube plug at end of piping and remove
dirt. Replace cap. Inspect distributing piping for damage and to see that
perforations are not clogged. Check all discharge lines and fittings for damage and-security. Coat control cables with grease, graphite, medium, Spec.
VV-G-671. (T. 0. 03-45C-1).
7. At first 50-hour inspection after installation, cylinders of CO., Fire Extinguishers will be removed and weighed to check for full charge. (T. 0.
16-20-2).
8. Lubricate cabin door locks and hinges.
9. Check contents of aircraft data case for completeness. T. O. 00-25-3.
I hereby certify that I have performed-supervised-the above inspections,
( Name, Grade and Duty)
(Orsaniaatioa aad Station)
SECTION 8-AUXILIARY EQUIPMENT.
11
BOMBING1. Grease bomb door operating units, bomb release slide, bomb control levers,
emergency z·e lease mechanism and bomb hoist pulley brackets as shown on
Fig. 3, T. 0. 01-20EB-2 (B-17B) and Fig. 4, T. 0. 01-20EC-2 (B-17C), see that
doors· operate freely.
•2. BOMB RACKS: Make detailed inspection of structure, installation fittings, releasing and arming mechanisms, and electric circuits for evidence
of wear or failure.
•s. 'Clean racks with kerosene, Spec. VV-K-211.
*4. BOMB RACK CONTROLS: Inspect all connecting members, mechanical and electrical, between control units and rack assemblies; check control
positions for proper relations throughout the system. Determine correct
operation with respect to both functioning and proper sequence of operation.
*5. Thoroughly clean entire control system.
4
�Page 19
100-HOUR AND SUBSEQUENT INSPECTIONS
Insert Serial No.
After Applicable Model
(Perform in addition to inapectiona of lnaer perioda)
B-17 ..................................B-17D ............... :............... .
B-17B ................................B-17E ............................... .
Orsanization ancl Home Station
B-17C ········-······················,B-17F ···················-··-·········
(Date)
INSPECTIONS REQUIRED
Remarks Pertainin•
to Defects,
Replacements or
Adjustments
Accompliah .c.-ne copy of the applicabie portion of thia form at each
JOO-hour inapection. Turn in completed forma to Orsanization
Enslneerin• Officer.
See T. 0. 00-20A ancl 00-20A-2
-· - - -· ·-
-·-- ··----- - -- - ···- - 1 - - - - 1 1 - - - - - - - - - - - - - - - -
2
1
3
SECTION I-ENGINES AND PROPELLERS.
27
MANIFOLDS AND SUPERCHARGERS.
Replace springs in Ball and Socket Tail Pipe Joints if the free length is less
than 4 5/8". T. 0. 01-20E-84.
29
...
POWER PLANT GENERAL-Check tightness of rocker box cover stud nuts. A void excessive tightness.
I hereby certify that I have performed-supervised-the above inspections.
(Name, Crade and Duty)
······-----· -- --············•--H ••••H••··········
---·,o~·•~-~-i~atioii·~~~f ·s~ti~~>·············
SECTION 2-FUEL AND OIL SYSTEMS.
FUEL SYSTEM1. Fill the seal chamber of the pump approximately half-full of grease,
lubricating, cup, medium. Spec. VV-G-681. Apply through Alemite or zerk
fitting in one of the ¼" pipe tapped connections next to the engine pad.
(T. 0. 03-l0EA-1).
35
FUEL TANKS:
ff
Check tanks for evidence of leakage.
I hereby certify that I have performed-supervised-the above inspections.
(Name, Crade and Duty)
-- - ·······································----····-----,o~-•·~·~·1~~·ti~~··~~~r-st·~•i~~>-············
SECTION 3-IGNITION AND ELECTRICAL.
22
SPARK PLUGS: Remove all spark plugs and replace with new, or newly
reconditioned plugs of same type. (T. 0. 03-5E-1).
I hereby certify that I have performed-supervised-the above inspections •
•
...............
( Name, Grade and Duty)
························································<o;:.;~·i~•·ii~n·~~~fst~t,~~>----·········
SECTION 4-LANDING GEAR AND HYDRAULIC SYSTEM.
37
TAIL GEAR-Grease retracting screw with thread lubricant, Spec. 3571.
38
WHEELS AND BRAKES: Raise airplane on jacks, and remove wheels
Check brake drums for scoring, undue wear, freedom from grease and oil,
loose screws; shoes and backing plates for distortion; return springs fur
proper tension and security. Check for cracked or loose bearing cups, scored
or cracked brake drum liners and. felt grease retainer for inboard bearing
for condition. Check for corrosion. Remove wheel bearings, thoroughly
clean and inspect for damaged rollers, races, or other defects. Replace any
defective parts and repack with the grease specified in T. 0. 06-10-4. Carefully inspect wheels for cracks, corrosion, damaged protective coating, etc.
Inspect casings for any signs of weakness, T. 0. 04-10-2. Adjust brakes on
reassembly. Check wheels after installation for end play, free running.
......
.....
4
�Page 20
100-HOUR AND SUBSEQUENT INSPECTIONS
1
2
3
39
CUN O HYDRAULIC FILTER: Remove filter from airplane and disassemble
sump from head and cartridge. Check cartridge rotation. Check that all
cleaner blades are straight and flat. Check that all discs are flat, evenly
spaced, and free from burrs or nicks. T. 0. 03-30-2.
ffff
39
Engine driven gear type oil pumps (Pesco). See that all pipe connections
are drawn up tight and pump installation properly secured and safetied.
(T. 0. 03-30CC-3).
4
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade ancl Duty)
(Orsanization and Station)
SEpTION 5-INSTRUMENTS.
44
NAVIGATION INSTRUMENTSCheck airspeed tube installation for leaks and voltage drop. Remove
drain plug in Airspeed tube installation and drain any accumulation of
water, T. 0. 05-50-1.
!.
2. Compensate compasses, T. 0. 05-15-1, 05-15-2. (To be accomplished at
intervals of not to exc,ed three months).
..,.
3. Bank and Turn Indicators. Remove instrument. Remove plug under
word "Oil" on the right side of the case. With a fine wire (.015) to guide theoil, lubricate with-If above freezing 8 drops of oil gyro instrument, Spec. . . . .
3563-If below freezing 8 drops of a mixture of 1/3 compass liquid, and 2/3
oil, gyro instrument. Remove drain plug at bottom of instrument near
front, to drain accumulations of oil and water. Clean screens. Reinstall
instrument and test suction-should be 1.80" to 2.05" Hg. (T. 0. 06-~0-2).
4. The vacuum supply to vacuum operated instruments will be checked at
each instrument to insure their correct functioning.
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Orsanization and Station)
SECTION &-MISCELLANEOUS
43
AIRPLANE GENERAL!. VACUUM PUMP: Check pump far security of mounting. Examine relief valve screen, if dirty remove the valve and loosen the screen assembly
with a wrench. Clean and replace.
2. Safety valve in line between Exhaust side of pump and oil separator of
de-icing system, remove the valve guide and wash in a suitable cleaning
fluid. If the valve disc is worn, dress it with a flat oil stone. Test. spring
tension (when compressed to 1¼ inches, must be 3.7 lbs.).
3. Clean oil separator (if removable screen) by removing oil outlet fitting,
removing screen and cleaning in a suitable cleaning solution. If without
removable screen, remove entire separator, thoroughly clean, using a s~itable solvent, dry with compressed air and reinstall. If equipped with vent
plug (plug marked PRESS) .remove and clean passage. (T. O. 03-30AA-1).
4. HEATING AND VENTILATING SYSTEM: B-17C-Remove and clean
cuno filter. B-t7 and B-17B-Drain system and flush as specified in section
4, T. 0. 01-20EB-2 for preparation of system for use.
5. Check microphones, connector coi:ds, flexible oxygen tubes, etc. for proper
anchorage in accordance with T. 0. 01-1-109.
32
32
FLIGHT CONTROL MECHANISM: Grease wing ftap control unit screw and
flap motor screw in accordance with Airplane Handbook.
fHHHt
,_ _ _ _ _ _ _ _ _ _ _ _ _ _ _
�Page 21
100-HOUR AND SUBSEQUENT INSPECTIONS
3
1
2
36
Cheek tension of control cables-if necessary to adjust see the Airplane
Handbook and T. 0. 01-1-9.
I hereby certify that I have performed-supervised-the above inspections.
( Name, Gracie and Duty)
(Orsanlution aad Station)
SECTION 8-A UXILIARY EQUIPMENT.
11
BOMBING: Grease bomb door retracting screw.
I hereby certify that I have performed-auperviaed-the above inspections.
(Name, Gracie and Duty)
(Orsanlutlon ancl Station)
16
PHOTOGRAPHIC: Lubricate tandem cradle rotating points with graphite
grease, Spee. 3692.
,
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
·
(Orsanization and Station)
150-HOUR INSPECTIONS
SECTION &-MISCELLANEOUS
43
AIRPLANE GENERAL: Flush out heating system (B-17C) ref. Fig. 38A,
T. 0. 01-20EC-2. and fill with fresh fluid.
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Orsanb:atlon and Station)
200-HOUR INSPECTIONb
...
SECTION 1-ENGINES AND PROPELLERS
28
29
Tighten propeller retaining nut ( if necessary).
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Orsanization and Statio11)
4
�Page 22
100-HOUR AND SUBSEQUENT INSPECTIONS
1
3
2
SECTION 2-IGNITION AND ELECTRICAL SYSTEMS
22
RETRACTING MECH'ANISM MOTOR: Remove and check clutch for slippage. The clutch for the landing gear retracting and flap operating mechanism shall be set as prescribed in T. 0. 03-5CC-1.
ff
I hereby certify that I have performed-supervised-the above inspections.
(Name, GnMle ••• Duty)
(Oraaalzation aad Station)
SECTION 3-IGNITION AND ELECTRICAL SYSTEM
22
FLUORESCENT LIGHTING: Check inverters for outputs and satisfactory
operation and starting of the lamp assemblies. Check auxiliary boxes for
output and satisfactory starting and operation of the lamp assemblies for
satisfactory operation (if ends of the lamps are dark, replace).
I hereby certify that I have performed-supervised-the above inspections.
(Name, Gr•••••• Duty)
(Oraani:ution aad Station)
SECTION 6-MISCELLANEOUS
32
FLIGHT CONTROL MECHANISM: Grease aileron, rudder and elevator
trrim tab controls in accordance with Airplane Handbook.
I hereby certify that I have performed-supervised-the above inspectiops.
(Name, Grade aad Duty)
(Oraanization and Station)
,r
�Page~
100-HOUR AND SUBSEQUENT INSPECTIONS
1
3
2
4
300-HOUR INSPECTIONS
SECTION I-ENGINE AND PROPELLER
26
VALVES.
1. Ch~k valve clearances. They should be .010".
2.
Ch~k for broken valve springs, washers. or other failures.
3. See that rocker box cover gaskets are in good c~mdition before closing
rocker boxes.
For valve adjustment instructions refer to Engine Handbook.
I hereby certify that ,I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Orsanization aacl Station)
SECTION &-MISCELLANEOUS
43
AIRPLANE GENEaAL:
1. Anti .. Icer and De-Icer Equipment, disassemble Eclipse air filter and wash . . . .
in gasoline. Lubricate all ball bearings in distributing valve with Tulc
Grease, Grade VH ( pack races only with the grease-do not pack gr.e ase in Hthe bearing cap). Lubricate all distributing valve gears and plain bea~gs
with engine oil.
-
2. Clean heating system boilers (B-17C). Unscrew nut on boiler core and
remove boiler core. Clean core with steam or hot water, dry thoroughly and
rep-lace.
32
400-HOUR INSPECTIONS
SECTION 4-LANDING GEAR AND HYDRAULIC SYSTEM
39
HYDRAULIC SYSTEM1.
Clean screen in bottom of oil supply reservoir.
2.
Replace valve core in pressure tank.
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
······ ·································· ··· ··· ·
·· ('Organi~atio~· and Station)
....,. ________________
�Page 24
100-HOUR AND SUBSEQUENT INSPECTIONS
1
3
2
4
600-HOGR INSPECTIONS
SECTION 6-MISCELLANEOUS
32
FLIGHT CONTROL MECHANISM: Grease elevator and rudder trim tab
controls in accordance with Airplane Handbook.
43
AIRPLANE GENERAL--
ff
RELIEF VALVES: Inspect and test landing gear, wing flap and other
pressure regulator relief valves and supercharger pressure reducing valve
for proper release pressure.
I hereby certify that I have performed-supervised-the above insp~tions.
<N-e. Grade and Duty)
(Orpniution and Station)
SEMI-ANNUAL INSPEC'l'IONS
SECTION 6-MISCELLANEOUS
43
AIRPLANE GENERALCheck all CO., fire extinguisher cylinders for contents by weighing.
(T. 0. 16-20-2). -
!.
2. Remove pneumatic life raft (if carried) from case or container, inflate
and test for leaks. (T. 0. 03-55A-1).
(T. 0.
3. Check CO., life raft inflation cylinder for contents by weighing.
16-20-2).
4. Test all installed safety belts except type B-11 (T. 0. 03-1-2).
03-1-15.
35
FUEL TA!'fKS :
03-1-15.
Inspect self-sealing fuel tanks in accordance with T. 0.
I hereby certify that I have performed-supervised-the above inspections.
·
(Name, Grade and Duty)
(Or•anization and Station)
ANNUAL INSPECTIONS
SECTION 6-MISCELLANEOUS
43
AIRPLANE GENERAL!. Check hand fire extinguishers type A-2 for proper operation.
03-45-1).
2.
(T. 0.
Test any type B-11 safety belts installed (T. 0. 03-1-2).
I hereby certify that I have performed-supervised-the above inspections.
(Name, Grade and Duty)
(Orsanization and Station)
, - - - - - - - - - - - - -·· -
�Page 25
AT ENGINE CHANGE INSPECTIONS
Jaaert Serial No.
After Applicable Motlel
B-11 ..................................B-17D ................................
Orsanbatlon -d Home Station
B-17B ·············-·················B-l7E ............................... .
B-17C ................................. B-17F .. ····················-···--··
(Date)
INSPECTIONS REQUIRED
Remark• Pertainins
to Defects,
Replacements or
Adjustments
Accompllab one copy of tlila form at each "Ea.ala• Cbaap" laapectioa. Tuns In completed t..nna to Orpnlaation Endneedas Olflcer.
See T. 0 . 00•20A -d 00-20A-2
3
2
1
Replace rubber vibration absorbers if condition or flying time warrant.
Lightly coat the interior of fittings, metal spacers and washers with castor
oil, prior to assembly of rubber grommets in mount. To tighten engine bolts
apply torque of 300 to 500 inch pounds. Make 1500-hour replacement of
rubber engine mount grommets at Engine Change naarest 1500-Hour period.
T. 0. 01-1-58.
43
See T. 0. 02-1-1 for preparation of engines for service following storage
periods of idleness or block test and preparation of removed engines for
storage.
When replacement pumps are available, all accessory pumps ( except those
with less than 100 hours.since last overhauled) will be replaced. This includes
De-le~ Pumps, Electric Motor Driven Pumps, Fuel, Oil, Hydraulic, Propeller, Anti-leer, Vacuum, and similar power driven units (T. 0. 03-1-4)~
24
Change oil (T. 0. 06-10-1). See T. 0. 02-1-22 for instrm:tions for pre-oiling
of engines prior to first start following oil change.
..
24
Prior to initial operation of engines equipped with automatic valve lubrication, fill the upper rocker boxes with oil. T. 0. 02-1-6.
**
21
Check marking of instruments to insure that they comply with T. 0. 05-1-16
and 06-1-17.
44
28
Swing compasses (T. 0. 05-15-2).
28
Check propellers for hours since last overhaul.
The propeller may be reinstalled, provided it meets visual inspection, and the
total time since last overhauled plus the maximum possible operating time
for the replacement engine does pot exceed 1400 hours. (T. 0. 03-20-5).
Partially disassemble and clean dome assembly in accordance with T. O.
03-20-5.
28
24
At every fourth engine change or any change made necessary by an interQal
engine failure of such an extent that metal particles are liberated into the
oil system, the oil tanks will be removed and cleaned and the oil system
cleaned as specified in T. 0. 03-15-10.
Ground Test and Flight Test in accordance with T. 0. 02-1-4.
I hereby certify that I have performed-supervised-the above inspections.
( Name, Grade and Duty)
( Orsanization and Station)
"'*
**
...,
4
�Page 26
lnaert s-ial No.
After Applicable Model
25 HOURS AFTER ENGINE CHANGE INSPECTIONS
B-17 ..................................B-17D ............................... .
(
Orpauatloa aad Heme Station
B-17B ................................B-17E ................................
B-17C ................................ B-17F ............................... .
o•
Zo
aZ
Ba
(Date)
INSPECTIONS REQUIRED
·h
Ullo
Accompliah one copy of thia form at fteh 112S-houn After Enslne
Chanse0 lnapection, Turn in completed form• to Orpalutfea
Eqlneeriq Offlcv.
See T. 0. Ckl-20A and 00-20A-2
1
2
.d.l
tJi:i
!!AJ
3
26
Check Valve clearances. They should be .010".
~
26
Check for broken valve springs, washers or other failures.
29
See that rocker box cover gaskets are in good condition before closing rocker
boxes.
**
**
29
Tighten thrust bearing retaining nut (if necessary)-using proper wrench
and applying torque of 600 foot pounds as prescribed in T. O. 02-1-34 • .
~
Inspect intake pipe packing nuts for tightness.
**
29
27
(T. 0. 02-1-28).
I hereby certify that I have performed-supervised-the above inspections.
(Name. Crade and Duty)
(Orsanlzation and Station)
,
Remarka Pertainins
to Defecta.
R%1acementa or
djuatmenta
.
4
�Page 27
ENGINE RUN UP INSPECTION RECORD
B-17F
Date___________AAF#__________Crew Chief_______
1.
2.
3.
4.
5.
6.
7.
a.
9.
Check hydraulic pressures
Main
.
Emergency
Parking and emergency brake
---------------Check
cyl.
head
temperatures
and
adjust
to outside air temp.
1____ 2 _ _ _ 3 _ _ _ 4
Check contents of fuel in tan
__k_s__
1 tank_ _ _ _ _ _ _ _ 4 tank
2 tank_ _ _ _ _ _ _ _ _ _ 3 tank - - - - - - - - - 2 feeder ________ 3 feeder
Total _____________ Total
--------Turn on fuel boost pumps and note pressures
1 ____ 2 ____ 3 ____ 4
Check instruments for operation and cockp~i-t-1-1-gh_t_s_
Test vacuum and other warning lights
LH
Check operation of cowl flaps
Check generators and note
Amps
Volts
--------RH
---------
1
2-------------3
4--------------
1
2 ---------------3
4 ----------------
10. Check inverter voltage
Normal _ _ _ _ _ _ Alternate _______
11. Check oil temperatures and note
1 ~_ _ _ _ 2 _ _ _ _ _ 3 _ _ _ _ _ 4
12. Check oil pressures and note
----1 ____ 2 _____ 3 _____ 4
13. Check
pressures
and
1 _ _fuel
__
2 ___
_note
3 ____ 4
14. Check
of_propellers
- range
1 _ _operation
__ 2 _
__ 3 __
___ 4 - - - - 15. Check engine switches L & Rat 25tt M.P.
1-L _ _ _R
_ _ _ _2-L _ _ _ R
3-L ___R ___4-L
16. Max. RPM & MP without
RPM 1 _ _ _ 2 _ _ _
M.P.l _ _ _ 2 _ _ _
17. Check turbo action at
___ R - - Turbos and note
3 _ _ _ 4 _ __
3 ___ 4
40" M.P.
1 - - - - - 2 - - - - - - 3. ______ 4
18. Check
and note cyl. head temp. during run up.
1 _______ 2 _ _ _ _ _ 3 _ _ _ _ _ 4
19. Idling RPM l _ _ _ _ _ 2 _ _ _ _ _ 3 ______ 4 _ _ _ __
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_012
Title
A name given to the resource
Inspections [guide issued by Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Inspection guide issued by the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. 31 typed pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Training
Extent
The size or duration of the resource.
31 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
documents
forms (documents)
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/fe556ba390506b93ba7033bfbdb1f743.pdf
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5.0
BES'l'RIC'l'ZD
Page 1
J'LYillG FORTBKSS SCHOOL
BOEDIG ~IRCRAJ''f COMP.ARY
B-17Y
S1'0DY GUIDE-IBS'l'BOMENTS
5.1
NAVIGATIOB DISTRUMDTS
1.
What 1s the :purpose of the magnetic compass?
2.
What is compass error?
~.
What is deTiation?
4.
DefiD.e the word variation.
5.
Name three
6.
What is the difference in the ettect of "hard iron• and •sort
iron• on the airoraft compass?
. 7.
causes or compass error.
When should the eom.paases be compensated?
ehecked before any attempt to compensate?
Shouli they be
a.
How much error is to be reaov•d trom the compass on N. and E.
headings.? How much on S. and W.? Why?
9.
'lhy should ammeters show maximum charge when adjusting or
compensating the com.pass?
10. 'lhen tlyiag due magnetic Borth, straight :t'light i •s maintained
by reterenee to what instrument?
These questions can be answered. from either the Technical
Order or the supplementary intormatio• on compass compensation.
HOT.I:
�BKSTBIC'l'KD
EYING YORT.BESS SCHOOL
BOEING ilRCRAn' COMPANY
B-17'F
5.0
Page 2
SUPPLDmNTABY INJrOBM4TIOB .. IBSTRtllEHTS
5.1 COMPASS COMPKNSATIOK
The purpose of the magnetie compass in an aircraft is to
enable the crew to determine the hea41.Dg of the aircraft at anytime. Tile m.agne·t1 ~-type eompe.as for use OJI. aircraft co:nsista
essentially of a liquid-tilled bowl contaiaing a pivoted float
element bearing a system of magnetized needles. The element ia
so suspended that the magnetized needles are tree to align them.selves with the horizontal oomponent ~f the earth's m.agnetio
field. In direct reading cmapassea, the position of the element
an4 its graduations, if any, are Tisible, with reference to a
lubbt>r-' s line, through a glass wiJUlow iJl the bowl. In remote
rea4~ oompasses, the positioa of the element is in41••~•4 by
a repeater system whieh toras part of the eompaas.
Direct rea41ng compasses tor use on aircraft are divi4e4
into two general types, Tiz., •B• type eampassea designed for
instrument board aounting an4 -i>• type compasses designed for
floor or table aounting.
Capass Brror: The error ot anr ooapaaa is the angular difference between true Borth an4 caapaas Korth. This angle is the
alpbraic sum. of the Tariatioa and the deTiation. These are
two terms cGDIJllonly used in conneotion with 0011passes that should
not be oontusecl.
a. Deviation - '!'he cam.pass leTiation is the 4ifterence between
hea4111.g ot the aircraft, as indioated by the compass, and
the actual magnetie healing of the aircraft. 'l'he deviation is
oalled »lus or minus (Bast or West, reapeotively) to indicate
how it aust be applied to the oom.paas Aea4ing to obtain the
actual magnetic h•adillg. The deviation, and its sign, is 4eterm.1ned by subtracting the aircraft compass reading trom magnetic
heading ot the aircraft.
the
· b. Tariatien - (1) Diflnitioa - Variation is the difference between the
lireotion indicated by an undisturbed magnetic compaaa and the
, true direction measured in relation to the earth's geographic
-•orth Pole. This dit~ers in Tarious localities an4 also ehangea
slowly, in particular loealities, fraa year to year.
(ll Tariation and the J.atro · COlll])aas - Yariation doe~ aot
matter to :,erso11nel engaged Ii the correction ot aircraft 0C11.passea unless they are usiq the astro campass, except insofar
as laying out ot the eoapass base may 1'e eon.eerned.
(3) causes of Compass Brrora - There are seYeral oauses
tor aaccuraey in aircraft eom»asaes; aam.ely, faulty installation,
Tibration, the aireraft'a magnetism (aetallio and eleotrioal)
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northerly turniag error and aeceleratioa error. Installat10Jl
and Tibration error can and shoul4 be corrected. Northerly
turning error and acceleration error are common in magnetic
needle type com.passes incorporating a aensitiTe elem.ant which
may be tilted and oannot be corrected. Errors eaused ~Y ,ha
aircratt's magnetism. should be oorrected insotar as ia practically possible. The aircraft eompass is oom:penaated to
accomplish this. Magnetism in aircratt which is likly t• ettect
the coapaas can be placed under three hea4inga.
(a) Hard Iron - This term is given to those parts of the aircratt which may be regarded as permanent magnets; that is, parts
in which the magnetism tends to remain the same. The effect of
hard iron can be determined with fair accuracy during a compass
swing. By the use of other permanent magnets (com_pensati:ng
magnets) near the com.pass, it usually can H compensated tor
eom.pletely. Once such oompensatioa has been accurately made,
it will reaain eftectiTe so long as t4e magnets do aot alter
their strength or position. If the compensation is not complete
and some error remains in the compass, the error will alter aa
the aircraft ehanges magnetic latitude. •or this reason, the
aocurate correction ot the aireraft'• permanent :magnetism i•
extreJYly important.
(b) Sott Iron - This term ia given to those parts of tre alrcrat~ wh1eh eontinuously change their magnetism, dependil'lg on
the influence ot other magnets (suoh as ear,11) on them. The
soft-iron m.agnetiBll will change as the aircratt•s headb.g ohallges
This magnetism. lrl.11 change the compass deviatio• with change ot
magnetic latitude if it results troa the preaenoe of llll&J11111.etrioal.
Tertical soft iron near the compass. The oompensatiOll or aa
aircraft eompass for soft-iron magnetism is ao eom»lieated aa
to be impraetical and shoul4 be pertoraed o•ly by an expert.
It is ilD.portant, therefore, that the 0011.pass location be such
that there is no soft iro• near it.
(c) neotrical KaffetiSll - This tera is given to th• magnets
by a lireot eleotrie ourrent flowing through a wire. Since the 41reot eurrent, oausiBg
electrical magnetism, is liable to ohange trequen'tly 4uriBg a
flight, it is ot the utmost importance that any single-pole
wires carryiBg a direct ourrent ahoul4 not paaa anywhere aear
the compass. If it is impossible to avoid this wiring, then
it is essential tbat tke wiri•g be ot the two-pole type. Kxperieaoe has ahoWil tha~ lhe use ot single-pole electrical wiring
near the compass has sueh a aerious effect that it 08Jlll~t • •
tolerated.
(aagnet!e fields) wheh are produee4
�RESTRICTED
FLYING FORTRESS SCHOOL
BOElliG AIRCRAFT COMPANY
B-17F
5.0
Page 4
STUDY GUIDE - msTRUMENTS
5.2 FLIGHT lliSTRUMENTS
1.
What checks are to be made on the Flight Indicator and
Turn Indicator?
2.
What general treatment or care should be given ·to all
glass covered instruments?
3.
What protection is provided for the air speed head?
4.
Are fuses provided for the electrical circuit tor the
Pitot heaters?
5.
What attention should be given to:
The holes in the air speed head?
The screens on the gyro instruments?
o.
What is the suction setting tor the Bank and Turn indicator?
7.
What is the color code of:
The vacuum lines?
The Pitot Static lines~
The Pitot Pressure lines:
a.
Name the instruments operating on vacuum.
9.
Name the Pitot Static instruments :
10. What Pitot Static instruments are mounted on the Bombardier
Navigator panel?
11. What is the setting for the vacuum warning lite switch?
12. What valves are located in the vacuum lines?
13. What is the setting value of the Suction Relief Valvei
5.3
ENGINE INSTRUMENTS
1.
What does the No. A.238 ret'er to? (WV"ing code) In answering give color·, length and size.-
2.
What is the tolerance of bend or a Tachometer Shatt in
making installations of tachometer shatti
3.
Where is the inverter located?
�RESTRICTED
5.0
Page5
5.5 ENGINE msTRUMENTS (Cont.)
4.
Is there more than one inverter?
5.
Is more than one inverter used at the same time?
6.
Is the inverter used to supply
7.
Does the inverter supply more than one voltage?
a.
What is the desired ruel pressure trom the engine fuel
pump as shown on the fuel pressure indicator?
9.
What 1s the desired oil pressure trom the engine oil
pump as shown on the oil pressure indicator?
n.c.
or A.C. Power?
10.
What could the manirold pressure gage indicator reading
be checked against?
·
11.
What is the tolerance ot the reading of the manifold
pressure indicator?
12.
What is the location of Fuse Shield #145?
13.
What capacity fuses are used to fuse the autosyn instruments?
14.
Do the Bus Bars on Shield #146 supply A.c. or D.C. power
or both?
15.
What power is supplied to the autosyn instruments?
16.
Should the inverter power be turned on before or attar
the ships engines are started?
17.
Should power be turned on while transmitter and indicator are not syncronized with each other?
18.
How many transmitters would be inoperative if ruse XXVI
blew out?
19.
How many power leads to eaoh dual indicator?
20.
It fuse XXVII blew out would the power leads (to the
dual indicators) marked E and B both be inoperative?
21.· Are terminals marked "A", "B", "E" all power leads?
22.
Which are ground leads, ir any?
�RESTRICTED
5.0
Page I
5.4 MISCELLANEOUS msTRUMENTS
1.
How often should the liquidameter (:ruelgage) tloat
position be checked for accurate indications?
2.
Where is the liquidometer fuse located?
3.
What is the capacity of the liquidam.eter tuae?
4.
Where is the free air temperature circuit :fused?
5.
What is the capacity of the tree air temperature ruse?
6.
Under what conditions should an instrument panel be
:pre-heated?
7.
How often should the tree air thermometer be checked?
a.
Whioh engines should be operated and at what R.P.M.
to oheck the de-icer pressure gage?
9.
How often should the de-icer pressure gage be oheoked?
10. How should a cylinder head temperature indicator be
checked?
11. How is the cylinder head temperature indicator adjusted?
12. A hydraulic pressure gage is not accurately readable
closer than a plus or minus how many pouncls?
13. What is the operating range on a hydraulic pressure gage?
14. Where is the cylinder head temperature indicator "red lined•~
15. What is the operating range on the cylinder head temperature
indicator?
i&. What is the operating range on the oil temperature indioators?
17. What is the ~urpose of the white line at the bottcn ot an
instrument :race?
18. How many liquidometer transmitters are there on the ahip?
1g. How many liquidameter indioators are there?
20. Ia the 2' Yolt current diatributed to the 11qu14ometer transmitters directly :rrC11L the bua at Shield Bo. l4e?
(
�RESTRICTED
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
5.0
Paga '1
TROUBLE CHARTS - INSTRUMENTS
ALTIMETER
Two type· C-12 altimeters on B-l 7F One on Pilot's panel; one on Navigators :panel.
Principle of operation - Absolute Pressure
Actuating Mechanism - Sealed Diaphragm
Altimeter·will measure air pressure or weight of air.
As plane ~limbs pressure decreases.
Aneroid diaphragm will expand and actuate pointers only.
This will indicate lower pressure in terms of increasing altitude.
As plane descends pressure increases.
Aneroid diaphragm will contract and actuate pointers only.
This will indicate higher pressure in terms of decreasing altitude.
Temperature changes are partially compensated by a bi-metallic spring.
So: Air pressure - altitude - temperature attect this instrument.
Checking altimeter (card)
Setting altimeter (:pointers)
Check card reading against station altimeter
Tolerance of• .015 in barometric pressure
If tolerance Ts exceeded, disconnect static line
Reset and recheek with line disconnected
If altimeter reads properly blow static line
If altimeter still has error - Reset card by
zero screw to correct barometric pressure.
PROBABLE CAUSE
REMEDY
Set pointers to field elevation
Tolerance or+ 15 ft. altitude
Consider height of inst. above field.
TROUBLE
.?n.strument gives an incorrect reading.
Instrument case leak
Out of calibration
Leak in static lines
Moisture in static lines
Remove and replace
Reset by zero screw
Cheak for leaks
Blow out static lines
Instrument fails to
register
Damaged mechanism
Restriction in static lines
Remove and replace
5low out static lines
Clean static vents
�5.0
Page 8
CLIMB INDICATOR
1 Type C-2 or A-7 indicator on B-17F on the pilots panel.
Princ'i!le of operation - Temporary differential pressure
letuat g mechanism - Diaphragm with capillary leak
Climb indicator will measure dif.ferential air pressure in climb and glide only
As plane climbs pressure will decrease
Diaphragm will expand and actuate pointer
This will indicate in term■ of a climb in thousands of feet per minute
As plane descends pressure will increase
Diaphragm will contract and actuate pointer
Thia will indicate in terms of descent in thousands of feet per mirm.te
·po'inter will return to zero in both cases in level flight
Diaphragm and case pressures will equalize through capillary leak
This instrument will indicate level flight and change in altitude.
Setting climb indicator - Vibrate instrument and reset to zero by screw adjustment.
TROUBLE
PROBABLE CAUSE
REMEDY
Inst. does not read 0
Instrument not zero 1 d
Out ot calibration
Adjust and vibrate simultaneously
Remove and replace
Inst. will not zero
Gears out ot meah
Remove and replace
Inst. too fast in operation Mechanism out ot adJustment
Inst. too slow in operation Moisture in static lines
Restricti~n in static
lines
Damaged mechanism
Inst. gives no reading
Leak in static line
Remove and replace
Blow out lines
Clean static vents
Remove and replace
Check for leaks
�AIRSPEED INDICATOR
2 Type D-7 or C-14 indicators on B-17F
5.0
Page g
One on pilots panel; one on Navigators panel.
Principle or operation - Differential pressure
Actuating mechanism - Open diaphragm
Diaphragm is connected to impact pressure and balanced by atmospheric pressure
As ~peed increases pressure will increase in pitot line
Diaphragm will expand and actuate pointer
This w111 indicate airspeed in miles per hour
Two pressures affect this instrument - Static (atmospheric) and pitot (impact)
When these pressures are equal pointer should read zero
Bavigatora airspeed pitot line connected to left· pitot mast
Pilots airspeed pitot line connected to right pitot mast
It indicator shows plus or minus reading disconnect both lines from instrument
Should now read zero; it not, replace.
'!'ROUBLE
PROBABLE CAUSB
REMBDY
Inst. reads ·high
on ground
Abnormal pitot pressure
out ot calibration
Blow out pitot line
Remove and replace
Inst. oscillates
on ground
Sock not on mast
Wind pressure
Protect mast until flight
Normal
Inst. reads low
on ground
Abnormal static pressure
Out of calibration
Blow out static lines
Remove and replace
Inst. not accurate
in flight
Leak in inst. lines
Out or calibration
Remove and replace
Check for leaks
Blow out lines
Blow out lines
• Bote:
Restriction in lines
Moisture in lines
Check against other indicator tor clue as to trouble.
�PITOT-STATIC SYSTEM
5.0.
Page 10 .
Two Type D-2 Pitot-static masts on B-17F - Blk. 2 left and right, lower fuselage
Source of pitot pressure is tube opening on pitot mast
Source or static pressure is 6 vents on each mast
Pitot lines from each mast do not connect with each other
Left line to navigators airspeed
Right line to pilots airspeed
Static lines connect in 4 way junction below navigators panel
Lett line to junction - Pilots static line to junction
Right line to junction - Navigators static line to junction
Extra static line to glide bombing panel and bombsight
Location or drains.
Two fwd. of blk. 3 left hand fuselage wall at floor level
Three at blk. 2
center line beneath plywood floor panel
Alternate static source.
Switch located on main panel, and on-oft switch on glide bombing panel
Pilots airspeed inaccurate if switch is in alt. source position
Selects static air from L. H. life raft it masts freeze
Pitot Heat
·
Switch located on pilots accessory p·anel, lower center
Used to free mast from ice formation
Check heaters for operation; do not overheat
Troubles
Restrictions - leaks - moisture - heater inefficiency
Trouble Shooting
•
Chee~ lnstrument tirst for correct operation
Then check fittings, lines, drains, mast.
Materials needed
3/16" I.D. Gum rubber tubing - 1/8" I.D. Hose fitting
(Standard AH 1/8" pipe thread)
Ohmeter, continu~ty light, 2 9/16" x 5/8" open end wrenohes, safety wire,
wire cutters
Operations
Leaks - Open static drain, insert hose fitting, attach rubber tube, seal static sources,
apply suction gently, pinch tube. (Never blow into instruments or lines}
Watch navigators instruments
Allowable drop 50 rt. per minute - altimeter; 1 MPH per minute - airspeed
Check tor instrument case leaks in same manner
.,
�5.0
PITOT-STATIC SYSTEM (CONT.)
Page 11
If system leaks, check inst., fittings, tubing, drains, selector valves.
Moisture
Disconnect all 5 instruments and proper drains, and blow toward mast.
Restrictions
Clean static vents with soft 1ire and blow out static lines
Clean pitot mast drain and blow out pitot line if necessary
Heaters
Check fuses for each mast at main fuse shield (146) Blk. 4
Use ohmeter and continuity light to check wiring and heater
Remove mast assembly and check heater plug.
*
Remove and replace mast assembly if masts are rough or peeled or
heaters are burned out.
�~.o
Page 12
FLIGHT INDICATOR
TYPE C-7
Will indicate attitude of plane 1n relation to horizon
Has a vertical gyro axis
Operational limits of 90 degrees 1n bank, and 70 degrees in climb or glide
Should be caged in violent maneuvers
Requires vacuum of 3.75 to 4.25 to operate with maximum efficiency
Has rotor speed of approximately 12,000 R.P.M.
When replacing instrument horizon bar must march bezel marks when plane is level
I.f not, file mounting holes to suit
Minimum coast check - Eight minutes
Attitude check - Should indicate attitude of plane when uncaged (2 - 6 ninutes)
TROUBLE
Fails to cage
Bar will not indicate
attitude
Bar fails to respond
Will not coast minimum
limit
PROBABLE CAUSE
Caging device incorrectly meshed
· worn pivots, unbalanced rotor
REMEDY
Remove and Replace
Remove and replace
Low or no vacuum
Open connections
Faulty vacuum pump
Adjust valve
Check vacuum lines
Check pump
Dirty filter
Clean filter
Worn pivots, bearings
Remove and replace
�5.0
DIRECTIONAL GYRO
Page 13
TYPE A-5
Will indicate amount of turn in degrees
Has a horizontal gyro axis
Operational limits of 55 degrees in climb, glide, and banks
Should be caged in violent maneuvers
Requires vacuum of 3.75 to 4.25 to operate with maximum efficiency
Has rotor speed of approximately 12,000 R.P.M.
Is used in conjunction with pilots compass to maintain true heading
· orift error check
With gyro operating, set card to 0
Uncage carefully and allow 5 minute run
Maximum drift allowable - 2 degrees
Minimum coast check - eight minutes
TROUBLE
PROBABLE CAUSE
REMEDY
Caging device incorrectly meshed
Unbalanced rotor (Pivot worn)
Remove and replace
Remove and replace
Low vacuum
Faulty vacuum pump
Open connections
Check instrument vacuum
Check pump
Check vacuum lines
Unbalanced mechanism
Scored pl vots
Low vacuum
Remove and replace
High vacuum
Clean filter
Instrument inoperative
No vacuum
Check vacuum, pump, regulator
lines
Will not coast
minimum limit
Worn pivot, bearings
Remove and replace
Falls to cage
Card spins continuously
Excessive drift
Check vacuum, pump, lines
�5.0
Page 14:
BANK AND TURN INDICATOR
TYPE A-8
Will indicate· direction or turn in degrees per minute
Gyro is much smaller and operates on horizontal axis
Vacuum restricted to 1.9 f .1 inch HG. (Check every 100 hours)
Regulated by restrictor screw at rear of panel
Has rotor speed of approximately 8,000 R.P.M.
In setting restricted vacuum, disconnect suction guage, remove case plug in bank
and turn indicator, and attach hose fitting and hose, other end of hose will be
attached to suction guage. Turn restriction screw to desired range and lock.
Reconnect all instruments properly.
Hand Position Check - .·o~ dead center.
Six mimites.
Tolerance 1/64 inch minimum Coast Check -
TROUBLE
PROBABLE CAUSE
Instrument pointer
not accurate
Low vacuum
Open connections
Faulty vacuum pump
Dirty filter
Adjust restriction valve
Check vacuum lines
Check pump
Clean filter
Worn pivots, bearings
Remove and replace
Instrument inoperative
No vacuum
Check instrument vacuum
Check pump, regulator, lines
Adjust restriction valve
Tolerance exceeded
Worn pivots, unbalanced
rot·or
Remove and replace
Will not coast ~inimum
limit
Worn pivots, bearings
Remove and replace
Hand
oscillates
REMEDY
�5.0
Page 13
DIRECTIONAL GYRO
TYPE A-5
Will indicate amount of turn in degrees
Has a horizontal gyro axis
Operational limits of 55 degrees in climb, glide, and banks
Should be caged in violent maneuvers
Requires vacuum of 3.75 to 4.25 to operate with maximum efficiency
Has rotor speed of approximately 12,000 R.P.M.
Is used in conjunction with pilots compass to maintain true heading
Drift error check
With gyro operating, set card to 0
Uncage carefully and allow 5 minute run
Maximum drift allowable - 2 degrees
Minimum coast check - eight minutes
\
PROBABLE CAUSE
TROUBLE
REMEDY
Caging device incorrectly meshed
Unbalanced rotor (Pivot worn)
Remove and replace
Remove and replace
Low vacuum
Faulty vacuum pump
Open connections
Check instrument vacuum
Check pump
Check vacuum lines
Unbalanced mechanism
Scored pl vots
Low vacuum
Remove and replace
High vacuum
Clean filter
Instrument inoperative
No vacuum
Check vacuum, pump, regulator
lines
Will not coast
minimum limit
Worn pivot, bearings
Remove and replace
Fails to cage
Card spins continuously
Excessive drift
Check vacuum, pump, lines
�VACUUM SYSTEM
5.0
Page 15
Vacuum pumps located on engines #2 and #3
Suction relief valves located in Nacelles #2 and #3
Maintain operating range for gyro instruments
Set at 4"
25 HG by thumbnut on valve
Pressure relief valves located in Nacelles #2 and #3
Provide escape for engine backfire pressure
Check valves located in Nacelles #2 and #3
Prevent pressure going to instruments
=•
Selector valve located on pilots sidewall
Will alternate source of vacuum from either pump
One pump operates De-icer boots
Other pump operates gyro instruments
Vacuum manifold is junction for instrument tubing
Suction guage will indicate amount of vacuum in flight indicator only
Vacuum warning switch located ' at rear of panel
Is regulated by screw adjustment in case to 3.75·-t .25HG
Warning light located above suction guage
TROUBLE
REMEDY
PROBABLE CAUSE
Vacuum pump not operating
efficiently
Low vacuum
Check vacuum pump
Suction changes with RPM
Spring in valve will not
move freely
Smooth out rough spots in
spring channel
Warning light operates high
or low
Contact screw needs adjusting
Remove cover, adjust contact
screw to 3.75 HG • .Do not
screw down lock nuts too tight
Suction cannot be raised to
operating level
Warning light fails to operate
Check all connections, lines
Wiring defective, fuse or
bulb burned out.
Check wiring, fuse (replace bulb)
Suction guage does not indicate
No vacuum
Check vacuum pump, connections and regulator.
Indicator hand oscillates
Damaged diaphragm-Fluctuation in suction relief valve.
Remove and replace-Check
spring in regulator-Remove
and bend spring- firmly nemlower end.
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_011
Title
A name given to the resource
[Study guides issued by Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Study guides issued by the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. Contains information about navigation, flight, engine, and miscellaneous instruments for the B-17F. 16 typed pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Boeing B-17F Flying Fortress
Training
Extent
The size or duration of the resource.
16 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
documents
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/6f7bc10d1e829c8c6bc72aea81e0ff9f.pdf
78d889f81729212993112b07bee51cd2
PDF Text
Text
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Page 1
FLYmG FORTRESS SCHOOL
BOEmG AIRCRAFT COMPANY
B-17F
SUPPLEMENTARY ELECTRICAL INFORNlATION-4.l
FACTS TO BE CONSIDERED m THE OPERATION OF A REVERSE CURRENT RELAY
Laws to remember
1.
(OHMS Law)
E -- Volts or pressure
I - Amperes, current or
amount of flow
R - OHM, A unit of resist-
~
ance
The magnetie force ot a coil - amperes x
ampere turns,
2.
# turns.
Called
3.
Any coil that is magnetized by having current pass through
the turns will have polarity.
4.
To
on
in
at
find polarity or a coil use RH thumb rule. The
the RH are wrapped around coil with finger tips
the direction that current flows. If the thumb
right angles to fingers the thumb points to "Ntt
N
Direction _,_
ot current
Direction
or aurrent
~
fingers
pointing
is extended
pole.
s
--+---+'
s
*DIRECTION OF CURRENT .AROUND COIL DETERMINES POLARITY
5.
If more than one coil is wound on a core and their polarity
is the 9ame you can add the {A.T., ampere turns, called
magnetic force). It their polarity is opposite then you
must subtract the magnetic roreea.
N )I
+
+
Lines of toree
:produced by
magnets with
like poles
travel in the
same direction.
Add the forces
in these two
coils.
Lines of force
produced by
magnets with
unlike poles
travel in
opposite directions. Subtract the forceas
of these two
coils.
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+ 24v
> - - - -.....
+
-----+24v
I
3.
These illustrations show the
relation of current flow in
regards as to the source.
1.
Generator and battery has
equal voltage. No current
flow.
2.
Generator voltage is higher than battery by one
volt. Hence we have one
volt pushing current through
oircuit resistance, generator is now source of power.
In this case generator voltage is less than battery by one
volt, thus battery is souroe. This illustrates the need ot
a reverse current relay. To automatically disconnect generator when it is no longer the source of power. That is,
when the line voltage is higher than the output of a specific generator.
This is fundamentally the circuit used to put generator on
the line. As the voltage of generator builds up the ourrent through coil increases the (A.T. or amper turns or
magnetic force). This magnetic force can be used to close
a switch and put generator on the line.
.,.
-;r:-
SPRI N'-
With the points closed coil is
now across the output or battery as well as generator. Now
if generator voltage falls below the battery voltage than
the battery becomes the source
and will keep coil magnetized
keeping points closed. Remember
current will take as many paths
as it can find back to its
source.
Now if we had a coil in series with the power line the reversal of current would change its polarity. If this series
ooil is wound on the same core as the other (shunt coil) we
can magnetiz~ or demagnetize the oore holding the points
closed.
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Page Z
As 1ong as the generator is the
source of power the polarity of
those two ooils is the same and
therefore the forces can be added
together to close and keep the
points closed.
Now suppose that the generator
voltage was increased to a point
where the current through the
two coils produced enough magnetizm to close the points.
l
It the generator voltage dropped
now the reverse current flow
would maintain the same ~olarity
on shunt coil and reverse polarity on series coil. The polarity
of these two coils are now opposite
when the two forces of these two
coils are equal the magnetic attraction for the relay points will
be cancelled allowing spring to
open the points thus stopping the
reverse current flow.
EXPLANATIONS OF HOW A VOLTAGE REGULATOR FUNCTIONS
1.
Review the rules mentioned in the · description of the reverse current relay.
2.
In addition remember the three factors that govern generator output.
a. Speed of conductors cutting lines of force.
b. Strength of field whioh produces these lines
of force.
c. The number of conductors in series on the
armature.
3.
The most practical way to control generator output is by
regulating the field s.trength according to generator
speed.
4.
According to ohms law it we put a variable resistance in
series with the field circuit, we could, by changing the
setting of the resistance, control the amount of cu~rent
flowing in the field circuit thereby controlling the output.
5.
Since the output of the generator varies with speed, we
can use this variation to set-u~ a variable magnetic
force which in turn can be used to control the setting
ot the variable resistance which is in series with the
tield.
.
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Page 4
6.
A
It the generator has reached the
desired voltage then any additional increase ot generator or voltage will push additional current
through the coils "A." increasing
the magnetism. This increase ot
magnetism will pull the bar down
_____.._.._..__putting the resistance in series
wi~h the field of the generator.
Now that we have this resistance
in series with the field, we can
add the resistance of the field
with the resistance of the regulator and we will find that we
will have less current flowing
in the field, therefore weakening the field and generator output.
7.
Now that the generator output has been lowered the current
in the coil "Att will be less, weakening the magnetic pull
on- the bar and allowing the spring to pull the bar back
shorting out regulator resistance which will allow more
current to flow through the field and which will raise
the -field strength and generator output.
a.
Bi-metallic strip - to compensate
for changes of spring tension
due to temperature changes. Dash
pot is a pneumatic shook absorber used to prevent oscillation
of shorting bar. Additional contacts from resistors to bar is
to give even regulation ·through
the useful engine speed range.
g.
10.
This regulator will regulate the voltage output of one
generator but when generators are used in parallel we
must have some method ot equalization so that one gener~tor will not hog the entire load.
40
35
30
'28.5
V
25
0
L
20
T
5
~~e~~~~~=--------A
------5
IS
/0
5
0
2.
S
5
O
7
.S
I
O
0
I
2
5
AM Pf:IU:5
I
S
0
I
7
5
2
0
0
Generator voltage output will
vary according to the amount of
current output, the reason for
this is that generators have a
small amount of internal resistance in its wires, when current
is drawn from the generator the
current flowing - through the internal resistance causes this
voltage variation. Generators
are just like any other piece
of equipment in the fact that
no two of them are the same.
These differences will affect
voltage output and therefore
we must use some system of equalization.
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(,'
11.
D
D
K
... :.17•·-~··ff,.\-.
_,..
~
•
. K-
4.0
Page 5
The adjacent diagrams show how
the equalizing system and equalizer coil is wired in the ship.
All "K" terminals of the equalizers are connected together as
shown. For confirmation check
the B-17F n.c. power circuit
diagram. The ground wires ot the
generators are so long that they
have a resistance of .0025 ot
an OHM. That ;means the curr·e nt
will return to the negative terminal from ground in as many paths
as it can find-in this case it
has four. Suppose generator #1
is putting out 200 am~s. and gen.
2,3 and 4 are idle. Then traoe
aurrent flow in the equalizing
circuit and you will tind thai
in gen. 2,3 and 4 equalizer coils
it will be going from "D" to "K"
but in gen. #1 equalizer ooil,
it is going from "K" to "D";
since these coils are wound the
same the polarity of coil in #1
will be opposite of 2, 3 and 4.
The resistance of the ground leads were .0025 so it generator
#1 were putting out 200 amps you will have 1/2 volt droi trom
ground to the negative brush of #1 gen. It generators 62, 3
SAd·_~ put out 100 amps a piece there would be 1/4 volt drol) in
these ground wires. Therefore, there must be 1/4 volt dirference in the negative terminals or #2, 3 and 4. When compared
to #1 generator. When this unbalanced condition exists between
generators then there will be an unbalanoed condition in the
equalizing circuit.
This unbalano~d condition in the equalizing system allows ourrent flow in the equalizers which will _affeo~ the out-puts ot
the generators throu.gh the regulating action or the voltage
regulators.
Since it takes an unbalanced condition between the generators
to make the regulators try and equalize the outputs, it oan be
readily seen that the generators will never equalize 100%
excapt at the point at which they are adjusted.
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Page 6
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMP .ANY
B-l?F
STUDY GUIDE -
ELECTRICAL
4.1 INTRODUCTION -- D. C. POWER CIRCUIT
1.
What ty~e of electrical system does the B-17 have?
2.
How many and what are the ratings of the batteries?
3.
Where are the battery toggle switches?
4.
How many generators are there on the airplane?
5.
Where is the A. C. fuse shield?
6.
How are the wires identified?
7.
On ships prior to 900 there were five master wiring diagrams.
What part of the airplane did each sheet cover?
s.
How many sllilplified diagrfills are there for each ship?
9.
Where are the electrical diagrams kept in plane?
10.
Name and give locations of six fuse shields?
11.
From ~ages 326 and 129 where in the airplane would you find
item t/156?
12.
Where in the airplane are items 1/215?
13.
How many inverters are there?
14.
In what circuit would you find the A.
15.
What is the fuse shield number in eaoh nacelle?
16.
Where are shields }146 and #305 located?
c.
voltmeter?
r
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Page 7
FLYING FORTRESS SCHOOL
BOElliG AIRCRAFT COMPANY
B-17F
STUDY GUIDE - ELECTRICAL
4.2 LOCATION OF ELECTRICAL EQUIPMENT
The electrical system of the B-17 is essentially a simple
one. However, it is such a large system that unless a systematic
visualization of it is gained, the beginner can become very confused.
In a broad sense the system breaks down into three divisions:
(1) the power input system (2) the distribution or wiring system
and (3} operational equipment.
The power input system and the wiring system were explained
in the first electrical lecture (4.1). Electrical equipment is
taken up in the second electrical class (4.2).
Experience has proven that the easiest way to become familiar
with the electrical equipment is to actually locate the equipment
on the ship. For this reason Class 4.2 is held in Hangar #2, where
an early B-17F is available.
To help the student investigate the electrical equipment in
the plane in an orderly manner, and at the same time make a record
of what he sees, a special guide has been ~repared.
This guide is made up of diagrams of the B-17, on which the
location of the electrical equipment can be plotted, and lists of
all the electrical equipment.
The student should locate as much of this material as he
possibly can before he comes to Class 4.2. Nearly all the necessary
information is given in the Technical Order.
After Class 4.2 the student will be held responsible for knowing the location and the purpose of all equipment listed in this
guide.
HELPFUL SUGGESTIONS
All unprotected or uninsulated uni~s of the electrical system
are placed in protective boxes, referre ~ to as shields. All shields
are numbered, the number appearing on both the shield and the wiring
diagrams. There are over 400 shields but only nine are of major
importance. The numbers and locations of these nine shields should
be memorized. The shields referred to are: 78, 79, 80, 81, 82, 83,
146, 243 and 305.
These shields all contain bus bars and wire junctions. In addition they may contain -ruses, relays and solenoids. A complete
knowledge of these nine shields and the units they contain is indispensible in trouble sb:>oting the electric system of the B-17.
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C
Page 8
4.2 LOCATION OF ELECTRICAL EQUIPMENT
HELPFUL SUGGESTIONS (Cont.)
Memorizing the locations of fuses would not be very profitable if it were not for the fact that by keeping certain general
rules in mind the location can be determined if a few exceptions
are remembered.
On the B-17 there are two ty_pes ·or circuits; namely, control
and power. Either or both could be fused. All control cirouits
are fused. Only a few power circuits are fused. All control
fuses are fused at station four with the exception of the battery
control fuses. Of the control fuses in station four, all are in
No. 146 except the carburetor air and windshield wiper fuses which
are in No. 243. Flaps, tail gear, hydraulic pump, landing lights
and carburetor air filters have the only power fuses and their
locations should be memorized.
Limit switches and solenoids will generally be found at the
equipment they control. The only exception being the flap solenoids. which are in the camera well, while the motor and limit
switches are in the left hand wing.
There are 35 solenoids in the B-17 whose location must be
memorized. Twelve of them perform a mechanical function. All
twelve are in the wings. Of the twenty-three elect~io solenoids,
eight will be found in the fuselage and fifteen in the nacelle
shields.
(
�B1CSTRICTBD
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Page 9
i-LYIRG ~ORT.RESS SCHOOL.
BOEDIG ilRCR.A.n' COMPilY
B-17Y
STUDY GUIDE - ELECTRICAL
4:.2 EQUIPMENT FAMILIARIZATION
Problem #1 - Indicate the location ot the tollowing items on
'the skeleton drawings ot the fuselage (Pages 11 and 12)
Shields - 82, 83, 146, 243, 305, 284, Generator voltage
regulator, throttle warning micro-switch.
Motors - Fuel transfer, hydraulic pump, de-ioer distributor valve, two prop anti-leers, bomb door, tail wheel.
Solenoids - Hydraulic pump, external poYer, tlaps, . tail
wheel.
Panels - Bombers, pilot's control, co-pilot's auxiliary,
main instrument
Miscellaneous - Bomb door satety switch, bomb rack satety
switch, agastat relay
Problem 12 - Indicate the location or the tallowing items o.u
the drawings of the inboard wings {Pages 13 and 14)
Shields - 78, ?9, 80, 81
Solenoids - ~our :ru.el shut ott, tour oil dilution, tour
starter meshing.
Miscellaneous - Two landing gear motors, tour reverse
current relays, two landing lights, one passing light,
three batteries, four ammeter shunts, four booster coils,
tour starter connection shields, tour fuel boost pump
motors
Problem #3 - Indicate the location ot the following items on
the shield diagrams (Page 15)
Solenoids - Four prop reathering, tour starter, tour
ret·r acting (main landing gear) three battery cutout.
Relays - Two landing lights, three throttle warning,
four carburetor air, one supplemental heat
Power tuses - Two landing light, ona tlap, one tail wheel,
one hydraulic pump and four carburetor air
Control ruses - Three battery cut-out, one carburetor air,
three windshield wiper and pump
�RESTRICTED
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Page 10
Prabiem #4 - Indicate the location ot the tollowing items on
the control penal drawings (Page 16)
Main instrument panel - Your prop feathering switches,
hydraulic and yaouum warning lights, red and green landing
gear warning lighl$•
Pilot's eontrol panel - Your generator switches, tour
ammeters, one voltmeter, one inverter nitch, three battery
switches, one landing gear warning switch, one hydraulic
pump switch
Central control panel - Your fuel boost switches, tour tu.el
shut off switches, tour magneto SYitohes, and one master
power switch.
Co-pilots .!llxiliary panel - Four oil dilution switches,
tour start and mesh switches
0
�4.0
Page 11
+
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Rl6HT HALF
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OF RAD/0
COMPARTMENT
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~.,.
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LEFT HALF AFT OF RADIO COMPARTMENT
A
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NACELLE- II
NACELLE- 1lI
0000
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STATION 4-
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805
THE- NINE MOST IMPOl2TANT 'SHIEL/JS-
�PANFL LOCATIONS
''A"
MAIN INSTRUMENT PANEL
\\ E."
PILOT'S CONTROL
PANEL
''D''
CENTl2AL CONT/20L
PANEL
''B''
CO-P/LOT:S
AUXILAQY PANEL
I
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�(,•
4.0
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Page 17
.FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F ,
STUDY GUIDE - ELECTRICAL
4.3
EQUIPMENT SERVICillG
1.
What are the identification numbers of the two types ot
generators used on the B-17? What is the capacity of each?
2.
Should generator bearings be lubricated?
3.
What is the difference between the F-2 and G-6 starters?
4.
llhat is the purpose of the adjustable button on the commutator end plate of the G-6 starter?
Why?
After adjusting th~ voltage regulators to the _ :proper _voltage
what is the allowable variation in load as shown hy the ammeters?
,I
•
Why is the use of a portable voltmeter recommended in making
V. R. adjustments?
7.
Referring to the generators, what do the following letter
symbols represent: A-B-E-K?
8.
Explain the proper mixture of fuel and oil for the auxiliary
power unit?
�{J
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Page 18
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-l7F
STUDY GUIDE - Q.UESTIONS
4.4
SECONDARY CIRCUITS
1.
The tr.ailing segment ot which magneto is ted by the
booster coil?
2.
When is the booster coil energized?
3.
Where are the hand crank and c:g:tensions carried?
4.
How is the starter controlled?
5.
At what pressure does the P.F. pressure cutout switch
open the cirouit?
6.
What circuit does the P.F. pressure switch open?
7.
Where is the P.F. pressure cutout switch?
a.
Where are the P.F. holding coils?
9.
Where are the following firewall connections:
(1) Starter
(2) Meshing
(3) P.F. Pressure
sw.
(4) High tension booster
coil lead
{5) P.F. Motor
10.
What circuits are included in the "0" oirouit?
11.
Looate fuel shutoff valves, ruses and control switches.
12.
What are the :t'uel boost ~um~s used for?
13.
Locate the following:
(1) Banbardiers suit heat and ruse
(2) Navigators suit heat and fuse
(3) Tail gunners suit heat and tuae
(4) Radio operators suit heat and ~~se
�RESTRICTED
FLYING FORTRESS SCHOOL ·
BOEING AIRCRAFT COMPANY
B-17F
STUDY GUIDE - QUESTIONS
4.5
RETRACTION CIRCUITS
1.
Where is the landing gear control switch?
2.
Why is the slip torque clutch used on the retraction motors?
Why is an engaging clutch used?
4.
Where are the limit switches for the main gear fuses in the
power circuit?
5.
Do the three landing gear motors have tuses in the power oirouit?
6.
Do the three landing gear motors have a fuse in the control
circuit?
f·
✓ a.
9.
What are settings for all retraction motor limit switches?
The tail wheel look lite will come on when the lever in the
cockpit i~ half way up. Where is the lite? What color is
it? Where is the switch that operates it?
Where is the switch and motor for the carburetor air filters?
10. When is the rirst inspection made on retracting motor units?
4.6
TROUBLE SHOOTING
4.7
SECONDARY CIRCUITS
(No preparation is necessary)
1.
What is the purpose of the throttle warning?
2.
When are the landing gear warning switches closed?
3.
Through what switches does the horn relay get its power?
4.
What switch stops the horn from blowing?
5.
When is the tail wheel look lite off?
6.
On what voltage do the bomb warning lamps operate?
7.
From what fuse panel do you get power for the fluorescent lites?
a.
How many bomb release lites are there?
9.
Why are there any fuses in, the nacelles when they can't be replaced in flight?
(Final electrical examination will be given in 4.7)
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_010
Title
A name given to the resource
[Study guides issued by Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Study guides issued by the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. Contains information about electrical system for the B-17F. 19 typed pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Boeing B-17F Flying Fortress
Training
Extent
The size or duration of the resource.
19 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
documents
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
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Page 1
FLYING FORTRESS SCHOOL
BOEING AIBCRAFT COMPANY
B-l7F
STUDY GUIDE - QUESTIONS
3.1 HYDRAULIC SYSTEM
1.
What units are operated by the hydraulic sy~tem?
2.
What supplies the pressure tor the system and how is that
pressure regulated?
3.
What units are mounted on the removable panel?
4.
How are the brakes bled?
o.
To .what sources can maltunotioning or the system be attributed?
6.
What precautions should be taken in the operation and servicing
of the hydraulic system?
7.
What size and type of tubing is used in the system?
a.
To what pressure should the accumulators be inflated and what
precaution should be taken?
g.
The
hydraulic system is pressure tested at what pressure?
l0.
How is the pressure relier valve checked?
11.
What is the proper procedure tor bleeding the cowl tlaps?
12.
What protects the pump against excessive pressures?
13.
What precaution must be taken betore disassembly ot the aooumulator?
14.
What is the purpose of the accumulator service valve?
15.
What is the purpose ot the two positions of the selective
check valve?
16.
What would an oil leak past the Schrader valve at the air compartment ot the accumulator indicate?
17.
By a simple line diagram, show the route of tlow trom the
pressure line through pil~ts and co-pilot's metering valves
out to the brakes and back to the tank.
18_.
What are the
19.
Cowl tlaps are adjusted to operate in how many seconds?
20.
Will a detective shuttle TalTe cause pressure to drop when
brakes are ~arked or unparked?
runctions of the return boost valve?
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, FLYING
FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
HYDRAULIC SYSTEM-TROUBLE CHART
TROUBLE
A. Hydraulic pump runs continuously or cuts in too
often with no change in
oil level in tank and
pressure on main gage below 800 psi •. Units not
being operated and main
system closed off from
emergency system by manual
shutoff valve.
PROBABLE CAUSE
REMEDY
1. Emergency relief valve seat
or poppet chipped or has
particle of dirt lodged
between poppet and seat.
1. Disassemble,check seat
and poppet and clean
thoroughly. Replace
valve it seat or poppet
detective.
2. Emergency relief valve set
too low.
2. Readjust to proper setting - see T.O.
3. System bleed valve on hydr.
3. Open valve three turns
4. No or very low air charge in
accumulator.
4. Preload both the main
and emergency accumulators to the speoitied
pressure.
5. Cheok valve on hydr. panel.
faulty.
5. I t the inspection indicates that poppet or
seat cannot be dressed
down replace valTe with
new part.
6. Internal leak in brake ·
6. It a tlow can be heard
thru any one or 'tlaa tour
panel not sealing tightly.
metering -valTe.
and then close tightly.
It -this doesn't stop a
detected flow through
this line remove valve.
Disassemble and check
seat and plunger tor
nicks or replace valve
outright.
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PROBABLE CAUSE
6. Cont'd.
6. main metering Tal.Tea when
the brake pedal la not
being depressed, de~ress
the adjacent brake pedal
three times. It this does
not sto;> the tlow check
for 15/16 dimension between
sli~ing sleeve and shoulder
on the lealcy valTe. It less
than that dimension when
the pedal is not being
depressed readjust the set
screw which bears on ihe
sleeve until 15/16"•1"
dimension is obtained. It
this does not remedy the
trouble replace valve.
7. Internal leak in cowl tlap
7. With a gage in the pressure
line to the cowl tlap nlTe
apply pressure to this line
and oheok opening pressure
of relief valve. If below
1200 psi readjust to this
tigure. It relier nlve can
not be readjusted the reliet
valve ball, spring or seat
may be faulty. In this latter case replace parts or
entire valn.
a. Check valves in hydr. hand
pump faulty or being held
open by d:1rt.
a.
valve from main high prets•
sure line to main retu~n ·lil).e
due to taulty or im.pro»eriy
adjusted relief valve (part.
- of large cowl flap valve).
It a tlow can be heard in
the lines attaching to the
hand pump operate the handle
a few times. It this does
not stop a detected tlow
replace the hand pump.
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TROUBL~
B. Hydr. pump runs continuous l.,r "\Jri th no change in
oil l 2vEi l in tank and
pressure on main system
gage above 800 :psi oil
relieving through the
emergency relief valve
(check by putting hand
on spill-over line from
relief valve).
c.
PROBABLE CAUSE
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REMEDY
1. Pressure switch out of
adjustment.
1. Readjust main points to
open at 800 psi or replace pressure switch.
2. Hydr. pump solenoid stuck
2. Free up solenoid or replace.
in closed position.
Hydr. ~ump will not start 1. Hydr. pump solenoid stuck
after hydr. :pressure on
open
main gage drops below 550 2. Pressure switch out of
:psi.
adjustment.
1. Free up solenoid or replace
2. Readjust main points to
close at pressure specified in T.O.
3. Check main and solenoid
3. Fuse burned out.
circuit fuses and replace
defective :ruses.
4. Pump shaft sheared or motor 4. If check of brushes show
them OK replace pump assy.
at fault.
D. Oil in hydr. tank and
lines gets very warm and
froths out tank vent.
1. See all probable causes
listed under Trouble "A"
and ''B"
1. See all remedies listed
Trouble "A" and "B"
E. System won't hold pressurel. See Probable Causes 1, 2,
over night - parking
brakes off.
3, 5, 6, 7 and 8 listed
under Trouble "A".
F. System loses :pressure ov.e r1. Internal leak
night when :parking brakes
valve.
set but does not lose
pressure when brakes not
set.
:in: metering
1. Determine whioh metering
valve is leaking, remove
and replace with new valve
or disassemble and oheok
internal ring packing (not
chevron packing) seat between piston and cone
shaped pintle. Rework or
replace any defective parts
and reassemble.
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TROUBLE
F. Cont'd.
G. System pressure up but
poor brakes or no brakes
when either the main
system or emergency
system used.
PROBABLE CAUSE
REMEDY
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Page 5
2. Defective packing in deboost
2. Replace valve or replace
valve evidenced by oil running
packing rings in defectout breather hole in back or
ive valve.
deboost valve on to oleo strut.
3. Deboost valve casting sweat
leaking.
3. Replace valve.
1. Air in brake line and expander
tubes.
1. Bleed brakes by removing
machine screw and loosening
3/8" hex at wheel fitting
and set parking brake.After
no air bubbles seen in escaping oil, tighten 3/8"
hex and replace machine
screw before releasing
parking brakes. Repeat,
holding emergency brake,
levers down instead of
setting parking brake.
2. Broken expander tube evidenced 2.
by large quantity of oil at
brake drums and sudden drop
in pressure when brakes applied.
Replace expander tube
making certain to bleed
brakes before taxiing or
flying airplane.
3 • . Broken line or fitting between 3. Replace failed part and
metering valve and expander tube
bleed brakes.
evidenced by oil excaping and
sudden drop in pressure when brakes
applied.
4. See Probable Cause No. 2
Trouble F
4. See Remedy No. 2 under
Trouble F
5. Shuttle val~e leaking from one
side or piston to other side.
5. Replace valve or replace
packing ring in valve.
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TROUBLE
G. Cont'd.
H. Dragging brakes
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PROBABLE CAUSE
REMEDY
6. Worn brake lining.
Page 6
6. Replace lining, when worn to
7. Brake lining glazed
5/16 on std. lining or 9/16
on heavy duty lining.
7. Roughen lining.
1. Insufficient clearance between
1. Lining should be turned or
brake drum and brake lining.
2. Deboost valve piston not
forced back up by spring
of grit between cylinder
ton or because of broken
being 2.
because
and pisspring.
sanded to
clearance
weight or
on wheels
is put in
give • 045 + • 005
with drum before
airplane is put
and before oil
ex:pander tubes.
Replace valve or disassemble
valve, clean and replace any
defective parts and reassemble.
3. Large particle of dirt like
3. Apply brakes violently three
thread shaving under ball check
times. If this does not stop
in metering valve or badly damaged detected flow thru valve, reball or seat in valvc,all evidenced place valve or disassemble to
by rapid loss of hydr. pressure or make sure a large particle of
continuous operation of hydr. pump dirt is not causing trouble.
Flow may be heard at metering valve.
I. Emergency brake sys- 1. Internal leak in emergency brake 1. If a flow can be detected
thru either of the emergencY
tem pressure drops too
metering valve.
metering valves when the
rapidly (emergency
levers are not being pulle~
levers not being used
down, give these levers three
to brake the airplane)
quick pulls. If this does not
stop the flow refer to the
T.O. to verify that the set
screw, on the end of the
brake lever, which bears on
the sliding sleeve of the
leaky valve is adjusted
correctly. If adjustment of
this screw is correct the
valve must be faulty and
should be replaced or reworked.
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Page 7
TROUBLE
I. Cont'd.
PROBABLE CAUSE
2 • .External leak in pressure lines
or oil side of emergency accumulator.
2. Tighten fitting or replace
3. Loss of air in emergency accw;n.u
3. Tighten valve core adapter
lator at valve core or seal between accumulator cylinder and
lower dome.
4. Leak in Selective Check Valve or
Selective Cheok Valve left in
"Servieen position with Manual
shutoff valve on top of main
accumulator in open position and
some sort or a leak existing in
the main system. See Probable
Causes listed under No. 1 of
Trouble "E".
J. Filter handle sticking
REMEDY
1. Filter has not been serviced
regularly.
tube and fitting tighten
bolts holding upper dome
to accumulator cylinder.
in accumulator dome, replace valve core if definitely leaking, tighten bolts
holding lower dome to
accumulator cylinder.
4. Locate and repair leak in
main system and replace
or repair selective check
valve. Manual shutoff
valve should alw.ays be in
the closed position unless
the emergency system is
being charged.
1. Remove, disassemble and
clean.
K. Pressure relief valve
1. Improper adjustment.
relieves about 950 psi.
1. Readjust to proper setting
(See T.O.)
L. Oil comes from air valvel. Oil leakage in accumulator due
on accumulator when it
to extremely low temperatures.
is bled down.
1. Recharge accumulator with
2. Oil leakage in accumulator due
to worn rings on piston.
air,make piston move up
and down several times
by raising and lowering
pressur1. This tends to
liven up the rings and
make them seal.
2. Disassemble and replace
rings or install new
accumulator.
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Page 8
TROUBLE
PROBABLE CAUSE
REMEDY
M. Selective check valve
leaking around shaft.
1. Shaft packing loose
1. Tighten packing plate·.
N. Brake metering valve
(main or emergency)
leaking around sliding
sleeve.
1. Defective chevron packing.
1. Replace packing or replace complete valve.
o.
1. Speed Control improrerly
set or filling with ~irt.
1. Loosen lock nut on speed
control and turn slotted
screw three turns in the
"Fast Direction". Operate flaps several times,
reset screw to give desired opening time for
flaps and tighten look
nut and safety.
1. Air in actuating cylinder.
1. Loosen tube nut on flexible hoses at cylinder.
Actuate cowl flaps to
allow oil to leak out
until free from air
bubbles.
2. Defective rings on cowl flap
2. Replace rings or complete
cylinder assembly.
Cowl flaps operate too
fast or too slow.
P. Cowl flaps creep open
or closed.
actuating piston.
Q, • Cowl flaps have bounc-
1. Same as P. 1.
R. Cowl flap cylinder has
1. Piston rod packing too tight
. ing motion.
chattering motion.
s.
and dry.
Cowl flap cylinder hits 1. Lock nut on left end of cylinder loose.
carburetor.
1. Loosen packing,lubricate
with hydraulic oil.
1. Loosen lock nut at left
end of cylinder,rotate
cylinder to' clear carburetor and tighten
lock nut.
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TROUBLE
T. Warning light tor either
the emergency or main
system comes on at a
pressure above or below
what it is su~posed to.
{See T.o. for correct
:pressure.)
PROBABLE CAUSE
l. Pressure warning switch out
or adjustment.
REMEDY
1. Readjust warning switch
or replace. (Note: The
emergency system warning
switch is exclusively a
warning switch while the
main system warning
switch is built integral
with the :pressure switch
which controls the hydraulic pump--be sure it
is understood which set
or contracts is for the
warning light.
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10
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
STUDY GUIDE - OXYGEN 3.2
1.
What type of bot _tles are used on the B-1 ?F Oxygen System?
.ffow many of eaoh?
2.
What type of regulators are used on the Oxygen System?
3.
Give the advantages of low :pressure oxygen system ov: high
:pressure system.
4.
What type and size tubing is used and what are the color codes?
5.
What is the duration of the bottle's su:p:ply?
6.
What is used to enable men to move around at high altitudes?
?.
What are the main "Don'ts" around the oxygen system?
8.
List cares to use in assembly and installation.
9.
Tell in your own words how to remove an oxygen bottle.
10.
What method is used in :pressure testing and locating leaks?
11.
List a general precaution to use when working on oxygen system~
12.
What thread lubricant is used?
13.
Give in your own words . a general description of the oxygen
system.
14.
Referring to the diagram, where are most of the bottles·
located?
15.
How are the turret bottles filled?
From what groups are they filled?
What sealant is used?
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FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-l?F
.
SUPPLEMENTARY lliFORMATION - OXYGEN SYSTEM 3.2
Most of the B-l?F airplanes have a demand type oxygen system
{A-12 regulators) installed in place of the A-9A regulators. This
system consists of a pressure gage and a flow indicator of the
· floating ball type in addition to the A-12 regulator. Incorporated
in the system are pressure warning lights that go on when the pressure of the oxygen is 100# or under.
The A-12 regulator, when the "auto mix" control is on, is completely automatic. It mixes oxygen with air, compensates for altitude _ and supplies oxygen only when the user inhales.
If the ~'auto mix" mechanism should fail to operate for any
reason, an emergency knob which will allow pure oxygen to flow to
the mask may be turned on. When this is used the "auto mix" control
switch should be olosed.
This demand system constitutes a considerable saving in oxygen
as the user has no control over the supply and can not use ' more
oxygen than is necessary.
There is also a walk-around bottle at every crew station which
has an A-13 regulator on it. This ,regulator is the same as the A-12
except that the auto-mix and emergency controls are lacking. The
walk-around' bottle may be filled from the main system through a
filler valve lopated at each station.
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FLYmG FORTRESS S.CHOOL
BO~ING AIRCRAFT COMPANY
B-17F
TROUBLE CHART - OXYGEN SYSTEM 3.2
TROUBLE
PROB.ABLE CA.USE
REMEDY
Regulators
No pressure reading
Defeative regulator
Clogged regulator
Replace regulator
Check distributor line
for pressure.
Inoorreot reading of flow
ln41cator
Restricted orifice
Remove and examine adapter orifice.
Unable to get oxygen from
adapter
Plugged orifice 1n adapter
Remove and examine
adapter oritioe
Regulator needle valve
stuck stiff or leaking
Needle valve needs lubricating
or cleaning
Remove needle valves
Lubricate valve and
threads and clean seat
Dual Check Valve
Entire system drains when
one bottle is removed or
punatured or filler line
ls leaking.
Cheak valves may be installed
backwards
Check valves may be restricted
Examine all check
valves and determine
.flow direction. Try
filling and releasing
pressure through filler
lines. Dismantle and
clean.
Bottles
Bottle does not warm up
like others
Bottle not receiving oxygen
Clogged or sticking check valve
Examine oheok valves
Replace if necessary.
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TROUBLE
General
System won't retain its
:pressure
PROBABLE CAUSE
REMEDY
Regulators not shut off. Connecting
nTees" leaking •. Plug in end ot
bottle leaking. Turret tiller valve
may be leaking.
Examine all regulators
Check with caatile soap
Check all bottles
Check turret bottle
adapters.
Flex hose leaking
Replace
Clean all above it necessary or replace
Leak around fitting
Flare broken
Parker fitting irregular
No Glydag aro@d sleeves
Re-tlare tubing
Replace
Re-lubricate
Leak around :pipe threads
Needs sealant
System won't retain its
pressure
Connections
Tin or apply litharge
and glycerin
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FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
STUDY GUIDE-ANTI-ICER SYST.1!34 5.2
1.
What is the purpose ot the anti-ioer system?
2.
a. Where are the anti-ioer pumps located?
b. What regulates the tlow of the system?
3.
Where is the anti-leer tank located and how can it be
4.
What fluid mixture should be used in the anti-ioing system?
5.
a. List several points to check during inspection period.
removed?
b. List several points to check during tlushing procedure.
(
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Page 15
FLYING FOR'!RESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
TROUBLE ·CHART-ANTI-ICER
TROUBLE
A. Incorrect output
B. Irregular flow or no flow
PROBABLE CAUSE
REMEDY
Bad rheostat setting
Make correct setting and
check flow.
Bad brushes in pump motors
Check and replace brushes
Faulty check valves
Replace valves
Bent lines
Straighten 1ines or replace
Glycerine jelled in tank and
lines
Flush with alcohol
Dirt or sediment in tank or
lines
Check tilter
Blow out lines-flush tank.
When pump is in operation it Replace pump.
should be checked for heat.
During the flushing of the
system, glyoerene is not used
therefore lubrication i_s l~cking. The same may be the . case_
while flying· if the -mixture ts
poor.
�(
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B99"17F
STUDY GUIDE-HEATil~G AND VENTILl.TION 3.3
1.
Draw a schemetic diagram- of the glycol circulation system.
2.
a. What fluid is to be used in the system?
b. Should any other fluids be used?
c. Wheri - ~hould the fluid be replaced?
7
3.
What --is the · proper re:plenishing :procedure tor filling the
glycol sy_s"-t~em?
-4.
What service does the filter require?
5.
a. What type ~ump is used?
b. How is it lubricated?
c. What is the . normal operati°Iig pressure and capacity of the
glycol pump?
6.
a. Why will the relief valve open when starting in cold weather?
.b. At what :pressure will the relief valve open?
7.
Should you repair a heater unit?
a.
What are the :positions to which the restrictors should be adjusted? Can they be adjusted in flight?
9.
Under what conditions would you remove the center heater?
10.
Why?
How would you adjust the damper control?
11. · How many vents overboard are there in the fuselage for the
ventilating system? Where are they located?
12.
How should the pilotts and co-pilot's air controls be adjusted
for best distribution of air?
13.
At what temperature does the glycol begin to break down chemically?
14.
Gfve. two reasons for the heating system?
15.
How would you flush the glycol system?
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Page 19
FLYING FORTRESS SCHOOL
BOEmG AIRCRAFT COMPANY
B-17F
SUPPLEMENTARY INFORMATION - HEATmG &. VENTILATION
GLYCOL FLUSHING msTRUCTIONS
Flushing instrµctions and replacement of the glycol at 150
hour intervals shall be followed in accordance with the following :procedure:
1.
Drain old fluid from system at pump and filter. Close tank
vents.
2.
Remove external lines connecting heaters (in exhaust stacks)
Remove heaters tram stack and clean cores, ch~bers and external part or the heaters, with a wire brush. If the inlet
and outlet ports are plugged, . they may be drilled out. Do
not attempt to remove pipe fittings unless damaged so that
they require replaoing. Check heaters and if -damaged exteaally {broken or deteriorated fins or worn guide tips} they
should be replaced. DON'T ATTEMPT TO REP.AIR OR PATCH T.B.1m
as the hazards from leakage or broken places are greater than
any saving~ accomplished.
3.
Remove and clean Purolator filter thorough1y. This tilter is
identical to same used in hydraulic system and may be tlushed
by: (a) Plugging inlet port.
(b) Removing cleaning plug tram the bottom.
{c) Applying pressure (steam and air) to outlet port. at
the same time turning tilter handle several times.
4.
It glycol system has been inoperative, remove pump from engine
pad and check drive tor being broken. and see that pump rotates
freely. Disconnect pump inlet and outlet lines at Nacelle firewall betore applying steam pressure.
5.
Apply steam pressure to return line at supply tank. Direct
steam thru return line until a good steady flow exists trom
connection at forward heater.
6.
Flush remainder ot lines with steam. Flexible hoses should not
be ~lushed with steam unless absolutely necessary as excessive
temperatures are detrimental to rlexible hose.
7•
.When system has been steamed thoroughly, blow out remaining
water using. air pressure, to prevent dilution of .gly~pl fluid.
a.
Beoonneat all units, except the pump, (using oildag at all
tube tittings) and ~lush entire system with clean fluid, the
type to be used, (55i diethylene glycol and 45% ethylene
glycol) tor service.
·
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Page 20
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
GLYCOL FLUSHillG INSTRUCTIONS, Cont•d.
9.
Disconnect auxiliary unit and connect :pum:p. Observe su:p:ply
tank and fill to proper level, with 55% diethylene glycol
and 45% ethylene glycol.
10.
Engines should then be started and the glycol :pum:p allowed
to circulate fluid. When engine is stopped, again oheok
tank and maintain the :proper fluid level.
ll.
Engine No. 3 should be run at approximately 2100 RPM and
31 inches of mercury manifold pressure, until following
items are accomplished:
(a} By inspection, determine whether fans on recirculating
air units begin to operate a few minutes aft.e r the
engine is started {Glycol should be at a temperature
of 1500F.)
(b) Disconnect electrical connections on recirculating air
unit fan motors to allow glycol temperature to increase
sufficiently (3oo°F.) to close thermoswitch which controls operations of non-recirculating air units.
(c)
(d)
By inspection, determine if fans on non-recirculating
air units will begin to operate within 15 minutes after
disconnecting recirculating air unit fan motor electrical
connection.
Reconnect recirculating air unit fan motors and check to
see if they operate.
12.
Run No. 2 and No. 3 engines at approximately 1700 BPM and 24
13.
Check operation of' air dampers as follows:
(a) Set dampers tor ttheat on• and see that all air is delivered
inboard.
(b) Set dampers tor "heat ott• and see that all air is
delivered overboard.
(c) See that dampers operate easily, without obstruction, and
remain securely in any set position.
14.
Check glycol level in tank and correct it necessary. The
presence of' water in the glycol system lowers its ettioiency
considerably inasmuch as the water boils out at the normal
operating temperatures or the system, thus diminishing the
inches of mercury manifold :pressure, then:
(a) Inspect to see if' all radiators are delivering heat.
{b) Inspect entire glycol system for leaks
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GLYCOL FLUSHING INSTRUCTIONS 1 Conttd,
the tank supply. It is important that items 7 and 8 of
the flushing procedure be adherred to .in order to remove
all :presence or water from the system.. Care should be
used when replenishing the system in order to avoid overfilling the tank. When filled to :full and boiling occurs,
vapor :pressure may cause an overflow.
EMERGENCY CLEANING PROCEDURES:
1.
Follow preferred method of cleaning system exce:pt hot water
may be :pumped thru the line in place of steam.
2.
When no auxiliary equipment ror cleaning is available, clean
as rollows: Drain glycol and reconnect lines. The return
line to the tank should be disconnected. The system is
flushed by running the engine at warm-up 5I>eed and at the
same time constantly adding water to the glycol tank. WAHNmG:
UNDER NO CIRCUMSTANCES SHOULD THE ENGmE BE RUN WI'IH THE
GLYCOL TANK EMPTY. When exhaust water is r1owing clean, stop
engine and drain the water :from the system. When possible,
blow lines out with air pressure then connect all lines.
Clean heaters and the filter and add :fresh clean glycol to
system as noted in :preferred procedure.
HEA'IBR CORE REMOVAL PROCEDURE:
1.
2.
Remove end oa:p.
Remove retaining :pin.
CAUTION: IF PIN IS EXCHANGED, IT MUST
ORIGINAL. {.94 long x .091 dia.)
BE 'lHE SAME LENGTH AS THE
Use a bolt and washers as shown to tree the core for removal.
4.
If the heaters are damaged externally {broken or deteriorated
~ins or worn guide tips) they should be replaced. DON'T
ATTEMPT TO REPAIR OR PATCH THEM, as the hazards . from. leakage
or broken places are greater than any savings aooomplished.
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Page
u
FLYING FORTRESS SCHOOL
BOElliG AIRCRAFT COMPANY
B-17F
TROUBLB CHART - HEATING & VENTILATING
TROUBLE
A. Glycol boils out
Steam from vent tube
PROBABLE CAUSE
Cool weather
Idling for a long period
Don't
Running engine with damper control Place in "OFF" position
in "HOT" position
Clogged air intake
Remove extraneous material
Warm weather
Intake air too warm to cool
radiator.
Improper fluid
B. No heat in cabin
REMEDY
No glycol circulation
Glycol tank & lines empty
Pump not operating
Heaters plugged
Filter clogged
Broken Qable to master control
valve.
Valve in "COLD" or "OFF" position
Restrictor valves wide open
Remove oenter heater.Replace with cover plate
Use approved tluid only.
Replenish, check tor leaks
Check tor sheared shatt
Clean heaters
Clean filter
Repair
Reset to recommended settings.
�3.0
RBSTBIC'fBD
Page 2'S
:rI,YIRG ~ORTRESS SCHOOL
BOBDJG ilRCBil'f COMPABY
B-17P
STUDY GUIDE - m:-ICER SYSTKM S.5
or
1.
What is the purpose
the de-icer system?
2.
What is the location ot the TacuUIB pUlllps and
source do they derive their power?
~.
How is the ncuum pump lubricated?
4.
a. What is the purpose of the rotary distributor valTe?
:r.rom.
what
b. Where is it located?
5.
'lbat is the purpose of the selector valve?
6.
Why is a pressure relier Talve and check Talve used in the
7,
When should the boots be oare:tully hlspeoted tor tears,
breaks or worn spots?
a.
Give the proper »rocadure for patohiJlg the boots.
9.
List five steps bl refinishiq the boots.
Tacuum line?
10.
What is the purpose of Prenite Graphite?
11.
Why m.ust the camouflage paillt be removed along the edge
of the wing surfaces before ms.t alling the booilaf
12.
Why must the boots be grollll.4ed after flight?
�BKSTRICTED
s.o
Page
l'LYIBG FORTRESS SCHOOL
a,
BOEIHG AIRCRAFT COMP.tNY
B-17-r
DE-ICER SYSTEM '!'ROUBLE CHART
TROUBa
PROBABLE CAUSE
RICMEDY
A.. Low pressure output
at low BPI(
One pump inoperative due to sheared
shaft
Replace pum}l
B. Bulging boots during
Pressure relier valve tails to release pressure (Boots pressure
tested tram 10 to 12 PSI)
Beaet spring tension
~r replace it valve
has trozen or tail•
to function amoothly.
c.
Worn brushes on motor ot diatributor valve
Sticky roter causing irregular
Ol)8ration
Change brushes
inflation period or
cells bursting
Irregular boot inflation
Change raters and
housing
D. ExcessiTe oil expelled
overboard thru line rrom
relief valTe in right hand
wing gap
Plugged orifice in drain line in
oil aeperator located in nacelle.
Oil by passing 41rty screen 1D
drain line.
Remove and clean
K. Small holes in boots
Static_ electricity
Keep boot well aoa'l--
Remove and clean
ed with Prenite Gra»h-
ite-it boot 1• too
badly damaged,replaoe.
P. Torn boot at rairing
atri]
Year due to camou:tlage paillt char-
Remove all camouflage
paint in region ot boot
attachment, before in-
Deterioration due to dry and hot
weather.
atalling boota.
ting boot during operation
I
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_009
Title
A name given to the resource
[Study guides issued by Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Study guides issued by the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. Contains information about the hydraulic, oxygen, anti-icer, heating and ventilation, and de-icer systems for the B-17F. 22 typed pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Boeing B-17F Flying Fortress
Training
Extent
The size or duration of the resource.
22 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
documents
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/5af8d70c158a00295c3da152780dd3dd.pdf
10264245a897292b5b26fe293d94560c
PDF Text
Text
-
;,;
t
RESTRICTED
'
,, '
2.0
Pagel
,
FLYING FOBTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17-P
STUDY GUIDE-ENGINE OPERATION
2,l
1.
Before starting the engines, in w~at position should
the tollowing controls be plaoed:
Cowl flaps
Fuel transfer valves and pump
Mixture control
Primer
2.
What is the maximum RPM and manifold pressure perinissible in the engine on the B-17F?
3.
List all the acoessqries on #2 engine on the B-17E.
4.
From the cruising control charts, what is _the _tuel
consumption tor all tour engines under the following conditions?
a. Gross weight 35,000#, engine RPM 2100, density
altitude 10,000 tt.
b. Gross weight 40,000D, engine RPM 2000, density
altitude 20,000 ft.
5.
From the long range orui~ing -chart, on page 70 in the
Operations Manual, what is the reoommended manifold
pressure and RPM under the tollowing oonditions tor
the B-17F?
a. Gross weight 50,000#, altitude 15,000 rt.
b. Gross weight 45,000#, altitude 30,000 rt.
o. Gross weight 60,000/J, altltude 5,000 :rt.
6.
List the steps in the :procedure to -feather Ill p~•\;pellar .
7.
What •are the proper cowl fla~ settings under the following conditions: start, take ort, climb, feathered
engine, landing and taxi?
a. Ir
after starting an engine no oil pressure appears
within 30 seconds what should be done?
9.
Where in the control oabin are the following controls
or instruments looatad:
Inverter switch
Cowl fla~ switches
Manifold pressure gaga
Fire extinguisher control
Throttles
Battery switches
De-icer valve
Heating system control
Starter switches
Fuel shut of f valve switches
�RESTRICTED
2.0 ·
Page 2
S~UDY GUIDE-ENGINE OPERATION 2.1
10.
What is the number of the engine used on _the B-17F
and what are its ratings under the following conditions? Take-oft, sea level and 25,000 taet.
11.
From the cruising control data on page 70 ot Operations Manual the best economy of opera·.,ion below
20,000 rt. is attained on an indicated air speed
ot ___ M.P.H.
l .,,
�2.0
Page 3
RESTRICTED
FLYlliG FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
PROCEDURE GUIDE - ENGINE OPERATI ON
PRIOR TO STARTING PROCEDURE
A.
SAFETY CHECKS
1.
2.
3.
4.
5.
6.
B.
AFTER ENTERING AIRPLANE
OPERATION
1. Adjust seat and rudder pedals
2. Check the hydraulic pressure
Pwnp up by hand pump it neoessary
3. Set parking brakes
WHY
For ease of operation of
brakes and controls
HOW ACCOMPLISHED
Adjustments
Read hydraulic gage
To keep airplane from creeping when engines are started
�ENGmE OPERATION (CONT. )
OPERATION
2.0
RESTRICTED
!!!!
Page 4
HOY ACCOMPLISHED
4. Check magneto and master switches To be sure no injury to
Visual oheck ot switches
tor "Ott" position
men or equipment results in tront or control stand
by accidental firing ot
the engine when the engin.e
is pulled through
5. Turn engine over 3 or 4 times
To clear lower cylinder ot Pull propellers through
oil or gaa accumulation
by hand. One engine at
a time only. So men will
not be hit by blade Gt
adjacent propeller
6. Throttles closed
To insure proper starting Manually move throttles
setting tor throttles
to closed position
7. Mixture control in idle cut-
ott position
Push mixture oontrol to
idle outoft position
a.
Supercharger control "OFF"
Pull supercharger control
handle in •OFF" position
9. Propeller control 1n low pitoh
(High RPM)
10. Cowl flaps open
propeller pitch controls to low pitch position
Keye
To be sure ground men will
have aocesa to rear of oylinders tor use ot tirebottles in case ot tire and to
gift bet~er ventilatien to
accessory section.
�ENGINE OPERATION (CONT.)
OPERATION
RESTRICTED
!!!I
2.0
Page 5
HOW ACCOMPLISHED
11. Intercooler controls in
"COLD" position
To insure proper cooling ot
air to carburetor from induction system
Move interoooler handles
to "COLD" position (in icing
conditions plaoe handles
toward "HOT"
12. Filter control 1n
position
To insure clean air entering carburetor
Plaoe switch in tilter •ON"
position and note position
of lights when »ower is on
13. Fuel boost pum~s in "OFF"
To be sure pumps do not begin to operate when power
is turned on
Place all fuel boost pUJJll)
switches 1n "OFF" position
14. ill electrical switches off
except hydraulic pump if on
external power
To be sure nothing electric- Check visually
al will operate when power
is turned "ON"
15. Heating system "OFF"
To be sure heating will be
inoperative during ground
run up. To prevent glycol
trom overheating
16. Surface De-icer "OFF"
To be sure surface de-ioers
do not operate when engines
2 and 3 are started
17. Flight control "Unlooked"
Tail wheel "Unlocked"
To be in complete control
of the ailerons and elevators at all times
8
0N"
Place surface de-ioers handle
in "OFF" position
�ENGINE OPERATION (CONT.}
OPERATION
RESTRICTED
STARTING PROCEDURE
!!!I
2.0
Page I
HOW ACCOMPLISHED
1.
Turn on external batteries
or ship's batteries
Pull red switch on external
battery cart "OUT" or in
"ON" position or switch on
shi~'s battery switches
2.
Turn autosyn inverter on
and check AC Voltmeter
Pull switch marked inverter
to "{Jptt or normal :position
Switch located on pilot's
lett on electrical panel.
Instrument should read
to ___ volte
---
3.
Turn on master ignition. switch
Magnetos are inOJ)erative Push master switch torward
with mas.ter swi toh in
in "ON" position
"OFF" position
4.
Set throttle for starting
So engine will receive
By pushing throttles torward
proper fuel air ratio
or toward Ol)en position.
to "catch" when started Approximately _ _ _" open.
5.
Turn on fuel booster pump for
engine to be started
Push boost pump toggle swi t .oh
which is located in tront ot
pilot on control stand, torward to the "ON" position.
6.
Turn on #3 fuel boost pump
Push #3 boost pump switch
forward or in "OH" position
7.
Set engine fire extinguisher
selector (If installed)
To insure use of exting- Set selector handle to engina
uisher in event ot tire being started (torward ot
in rear of engine
co-pilot)
�2.0
Page 'I
RESTRICTED
ENGINE OPERATION (CONT.)
HOW ACCOMPLISHED
OPERATION
a.
. 9.
All olear signal given
To be sure no one is in track
or ~rop blades and all ladders
and equipment has been moved
away from ship •
~rime engine (at same time To prime cylinders (Top 5)
co-pilot does #10).
Verbal veritioation trom
ground crew.
Push down on primer selector handle and turn to engine
being started. Pump several
times returning pump down to
olosed osltlon to prevent
over pr ming. rt pump ls
iett up, boost pressure will
cause fuel to be continuously yum.pad through primer
to eng ne.
1
10. Energize Starter
11. Mesh starter to engine
To furnish inertia power to
turn engine over. With G-6
starter-hold in "energize"
position while accomplishing
operation Ill)
To oonnect inertia wheel to
. engine by energizing starter
meshing solenoid
Turn Mag switoh to "Both"
position.
12. Turn on Mag. switch for
engine to be started
13. Operate primer as engine
startes if necessary
To furnish ruel to engine
until engine starts operating l.)roperly.
Pump primer up and down
until engine is operating
properly. When assured that
engine has "caught" push
primer down and turn to
"Ott" position.
�RESTRICTED
2.0
Page 8
ENGINE OPERATION {CONT.)
OPERATION
HOW ACCOMPLISHED
14.
Set mixture control in
.luto-Rich
15.
Cheak oil pressure and it
it is all right increase
BPK to about
To verify that oil pump and Cheok visually oil pressure
system is functioning proper-gage on instrument panel.
ly. RPM increased to allow
Pressure should normally
engine to warm up.
reach
to
lba. in 10
to 12 secondi7 If not SHUT
OFF ENGINE by moving mixture to •idle out ott".
16.
Check BH4
Avoid overspeeding
Visual (about 1000 RPM)
17.
Observe tuel pressure
To insure proper operation
Cheak visually fuel pressure
gage {pressure should increase immediately as engine
is started) Pressure should
be between ___and _ _ _ •
18.
Observe cylinder head
temperature
To check operation of inCheok visually head tem»erastrument and to control head ture gages (normally these
temperatures with cowl flaps.gages won't show temperature
increase until engine has
been running tor a tew minutes.)
·
19.
Obsorve oil temperature
To insure proper Ol)eration
ot oil cooling system and
OP.eration ot instrument.
Visual check ot oil temperature s.as• atter tew minutes
ot running. Should be be•
tween
and _ _ _degrees
20.
Observe manifold pressure
To be certain instrument is
o»erating and to see if
engine is running pro~erly.
Cheok visually manitold
~ressure gage.
---
Pull mixture handle trom
"idle out off" back to
"automatic rich position"
when engine tires.
of engine driven tuel pump.
�ENGmE OPERATION (CONT.)
OPERATION
RESTRICTED
COCKPIT PRE-FLIGHT CHECK
!!!I
2.0
Page 9
HOW ACCOMPLISHED
1.
Check flight controls
To be positive all control surfaces move correctly. Check tabs.
2.
Check lights
To be sure of correot operation
3.
Wing flap operation ·
To be sure of correct o~eratlon
4.
Observe vacuum suction
(Engs. _
and _
To be sure vacuum pumps and
system ls functioning correctly.
5.
Observe operation of
surface de-icers
To see that de-icer system ls
working correctly.
6.
Observe heating system
operation
To see that heating system ls
functioning properly
7.
Check flight instrumflnts
See that they are in good condition
8.
Check generator voltage
To see that generators are
operating
9.
Exercise blower handle
Turn on all lights that oan
be seen and check
Turn on de-icer switch and
observe operation or all
the de-icer boots. Observe
pressure gage ( to )
Turn heating system control
to "HOT" and as soon as
heat is observed turn system "OFF". Caution Do not
leave in "ON" position when
on the ground.
Check for broken glass,
markings, eto.
While engines are warming
up move supercharger handl•s
forward and backward slowly
This allows warm oil to circulate through supercharger
regulator.
�RESTRICTED
ENGINE OPERATION (CONT.)
OPERATION
WHY
2.0
Paga 10
HOW ACCOMPLISHED
10. Check cylinder head temp- To be sure head temperatures are Check visually degree
eratures
high enough to make engines run
up test.
or
head temperatures. The normal range is from 160° c.
to 205°c. Never allow head 0
temperature!
20R
c. on groun. toConetcerd
ro hea
temperatures by opening or ,
closin§ cowl flaps, 100° c.
to 190 c. preferable.
11. Check oil temperature
To be sure oil temperature is
high enough to allow engine to
be run up.
Operating range of oil temp~
is _to_; oil should be at
least 5o 0 c.
12. Check both mags. & "OFF"
position at low speed
To be sure Mags are operating
"OFF" position grounds out
mags.
At 700 to 800 RPM turn
switch to 11lffght" to "Left"
to "Off" then back to "BotH4!
&.
13. Check magnetos at from
_to_RPM.
Move magneto switch from
"Both" to "Right" then
back to "Both" then to
left and back to "Both"
14. Check propeller governors To be sure prop governors are
operating properly
Run engines up to
to
_RPM. Move propeller
goyernor handles to high
pitch position. Prop should
govern down to
RPM. Then
move handle back up to low
pitch position and RPM
should increase back to
original ·RPM
15. Check operation of Turbo
Supercharger
To see if turbo is operating
satisfactorily.
Run engine up to
"in
tull boost. Pull oack boost
control and manifold pressure should drop __"or_"
�RESTRICTED
ENG]!E OPERATION (CON'!:. l
2.0
Page 11
HOW ACCOMPLISHED
OPERATION
16. Full throttle run
.,
To be sure engines are turning
up properly and all instruments
are operating properly.
I
NOTE:
Open throttles slowly to
wide. open position and take
readings of manitold pressure (approx.
to
RHl)
Approx.
to -it'PM)oTl
pressure(
to lbs.) oil
temperatur"(-to
)
fuel pressure (
to
lbs.)
cylinder head temperatures
(
to
C). Generator voltages (Approximately · ) Generator . Amperage (showing
Charge.
Do not leave Generators on while operating on the ground..
17. Full throttle, full
boost run
To determine that full military
power is available
Place boost control ON slowly, open to tull throttle.
Tachometer should indicate
RPM. Manifold pressure
should be ___•.
18. Idling speed check
To determine that engine idles
•p roperly
Close throttles. Tachometer
should indicate
RPM
Manifold pressureshould
not exoee4 - " •
�a.o
BESTRICTBD
Page 18
ENGINE OPERATION (CONT. }
PROCEDURE FOR THE CLEANmG OF FOp:LED PLUGS
BY tilt USE MT
or
Increase cylinder head temperature by some ot the following methods in the order mention•~•
1.
2.
3.
NOTE:
BE VERY CAREFUL NOT TO INCREASE THE cn.INDER HEAD TEMPERATURE OVER 205°c •
PROCEDURE FOR SHUTTING DOWN AN ENGINE
OI'ERATIOB
WHY
HOW ACQOMPLISHED
1.
Check cylinder head temperature and bring dolril to
_ _approximately.
Engine should never be shut
down when very hot.
Cheok instrument and bring
down temperature bf _ _ __
2.
When correct temperature
is reaohed set throttle
to give approximately
Bever run engine too taat
when shutting down
Set throttle oontrol.
_RPM.
3.
Move mixture control to the
_ _ _ _ _ _ __,position.
Move mixture control.
••
Open throttle as engine dies
out to the wide open position
Mon throttle control.
�0
Page 13
-
HOW ACCOMPLISHED
1HY
OPIRATIOB _
I.
a.o
BESTBIC'l'ID
INGID 0fBRATt0N (CONT.)
Shut ott mag. switch when
engine bas stop~ed turning
To ground out the JDS.petoa
Move awitoh
It all engines are stopped the master awitoh and the invertor arltoh may be
shut off after instruments are dead.
PBOCEDUBE
1.
m
CASE OF FIRE IN ENGillE
(Betwee~ Engine
&Firewall
ot Nacelle)
2.
3.
4.
5.
6.
'I.
a.
LONG PERIOD CHECKS
The tollowing ehecks should be made approxlmatel7 onoe a month or when troubles
have been reported.
1.
2.
3.
4.
CHECK OIL DILUTION SYS&
�RBSTBIOTBD
l'LYIRG J'OB'l'BESB SCHOOL
BOBIRG AIRCRU'T OCIIP.A.RY
B-lff
S~Y GUIDB-mDUC'?IOR
SYSTBII @,I
1.
Deaoribe ih• oour•• ihat air un4er raa p~•••ur•
tollowa to get to the oubure,or.
2.
In what duo~ system is the relier YalTe looaied
and wh7 ie it there?
I.
How does the exhaust gas pressure operate th• ·
·. · auperoharger?
/
.·, .·.
,•.
.' 5.
What controls the exhaust gas preaaure?
How is the temperature or the air that gc,ea through
th• auper•harger reduced?
6.
Bow oan the olearanoe between th• nozzle box e4
turbine wheel be ·ohange4?
7.
Bow 1s autcaatio regulation ot th• auperoharger
aooampliehed by the superoha:rger regulator?
-e.
Where are the regula,ors tor the outboard and inboard
auperoharger looated?'-
What eaution should be observed in oonneetiag the
oil lines to the eu»eroharger regulator?
10. Where oan th• inboard and outboard :tilter elemel\t•
be reached tor removal?
�0
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2.0
Page 15
' FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-l?F
PROCEDURE GUIDE - INDUCTION
ADJUSTING SUPERCHARGER REGULATOR
1.
Kove the blower handle to give 46" ot Hg manifold pressure at
2500 R.P.M. with tull throttle and screw the stop out to engage
the blower handle and set its forward movement. Caution: Do
not run engine at this setting for more than thirty seconds.
2.
Stop engine in the usual manner and after engine 1s stopped move
the blower handle against the stop on the control stand where 46"
of Hg. was obtained and lock.
3.
Disconnect the linkage tram the bell crank to the supercharger
regulator at the bell crank. Also disconneot the positioning
spring cartridge at the bell crank.
4.
In the cockpit, unlock blower handle and after setting stop to
show 3/8" of thread between the angle that the stop ia held iJl
and the head of the stop itself, move the ·control handle against
the stop and lock.
5.
Adjust linkage at the bell crank and reconnect to the regulator.
6.
To set positioning spring cartridge to give 60% in oase control
cables are broken move blower handle back 1.6 inches measured
along the top ot the control stand :rrom the head of the stop to
the front of the handle.
7.
Adjust cartridge to line up in adjustment hole in the bell crank
and reconnect.
�RESTRICTED
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Page . 16
FLYmG FORTRESS SCHOOL
BOEING AIRCRAFT COMP.ANY
B-17F
TROUBLE CHART-INDUCTION
SUPERCHARGER AND REGULATOR
Trouble
No supercharging indicated
Probable Cause
Remedy
RefWlator Inoperative
Linkage binding
Cheak all linkage and
allow pro~er olee.ranoe
Restriction in oil inlet
line to supercharger
Check tor tree tlow ot
all
Lines crossed at engine
or regulator
Check all lines tor
proper position
Defective regulator
Replace with new regulator
Restrictor tee on regulator
inlet line reversed
Remove and install correctly
Wastegate
Inoperative
Stack stub may be damaged or
warped
Replace stack stub and
Wastegate linkage may be
frozen from lack of lubrication
Replace assembly
Wastegate may be bent or
broken due to backfire
Replace assembly
wastegate assemblJ
�2.0
Page 17
Remedy
RESTRICTED
Trouble
Probable Ce.use
Wastegate control on regulator
may be deteotive
Replace regulator
Detective Turbo-SuRercharser
Turbine blades damaged or broken Replace supercharger
Nozzle box exploded
Replaoe supercharger
Bearings frozen
Replace supercharger
'l'urbine binding on nozzle box
Repair by shims or replace
Intake duct broken or leaking
badly
Erratic supercharging action
Too low or too high manifold
pressure from supercharger
controlling
Regulator balance line restricted
Repair
Clear balance line
Binding on linkage
Cheak tor freedom of
action
Leaks in induction system
Repair
Erratic oil pressure to regulator
Warm oil in case or
cold weather by exercising blower controls
Leaks in exhaust system
Repair
Defective regulator
Replace
Improper adjustment on regulator Readjust the regulator
controls
Improper wastegate clearance
Adjust
�RESTRICTED
Trouble
Probable Cause
2.0
. Page 18
Remedy
Restriction in balance line
Clear line
Balance line broken or disconnected
Repair 'or replace
Faulty regulator
Replace regulator
Runaway turbine
Throttle back
Supercharger failure Bearings siezed
No lubricating oil in turbo lube tank
Keep tank tilled
Overspeeding ot turbine in flight
Stay within speoitied llm.1:ts·
Turbine siezed or broken
Insufficient clearance between turbing
Maintain proper clearance
and nozzle box or turbine and cooling cap-at all times or replace
Foreign material in turbo such as nut,
bolts, rocks, etc.
Nozzle box exploded or expanded
Change supercharger aa
soon as such a condition
is noticed
Wastegate not operating properly due to
improper lubrication or inspection
Check daily tor operation
Backfire with wastegate closed
Replaoe turbo
Supercharger housing failure
No clearance or play in exhaust ball
and slip joints
Allow proper clearance on
installatioll and check daily
Defective housing
Replace
�BESTRICTED
a.o
Page 19
PLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
STUDY GUIDE-J'UEL SY8TEM 21 0
l.
What type of fuel tanks are used on 4'h• B-17P'•?
2.
How many wing tanks are
3.
Where are the tuel tanks located?
4.
What are the capacities ot eaoh?
5.
Where would you find the necessary information on
cleaning and repairing or fuel tanks?
6.
What is the purpose ot the ·fuel booster pumps?
7.
Where are the booster pumps looated?
a.
Whioh booster pump provides ~ressure tor tuel priming?
9.
What is the purpose ot the em.ergenoy fuel shut-ott
TS.lves?
there?
10.
Give ~he location ot the tuel shut-ott valves.
11.
GiTe the looations ot the strainers in the tuel
system.
12.
What are the inspections on the strainers 1n the
tuel system? .
13.
With the right bomb bay tank empty, how would you
transfer tuel from the lett bomb bay tank to nUDlber
one tank?
14.
What is the oapaoity ot the bomb bay tanks on the
B-17F?
15.
What is the 25 hour inspection on the boost pump?
�RESTRICTED
2.0
Page 20
rLYmo FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-177
STUDY GUIDE-OD, SYSTEM 2 1 6
1.
Give the locations ot the oil su~ply tanks on the
B-171'.
a.
Give the oil tank capaoity, peroent ot expansion
apace and number of vent lines tor one oil tank.
3.
How is the shutter operation on the oil temperature
regulator controlled?
4.
Why do the shutters on the oil temperature regulator
oscillate?
5.
How is oil dilution accomplished?
6.
Explain the oil flow in the hopper type tank.
7.
What tY:Pa of oil tank stick gage is used on the B-17F?
a.
Where is the oil stiok gage located?
i.
What specification ot oil is used on the B-17F?
10.
What is done with the oil temperature regulator at
any engine ohanga resulting from engine failure?
11.
Describe the emergency repair procedure tor the radiator tubes 1n the oil temperature regulators.
12.
Give the locations
on the B-l7F.
or
the oil temperature regulators
r
�RESTRlr :.~~
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMFANY
1.0
Page 21
B-17F
STUDY GUIDE-ENGIRE MAINTENANCE 2.8
1.
lhat is the ditterenoe b~tween tli• R-1820-&~ engine and the
R-1820-97?
2.
How many valve s~rings are used on eaoh Talve? To prevent
these s~rings from sooring or eating into the aott aluminum.
head, flat steel washers are uaed under what springs?
3.
What is the approximate 'capacity of the sum»?
4.
What two :provisions are made in the sump tor keeping toreign
material rrom entering oil circulation?
·5.
What is the purpose ot the two vent lines at the top ot the
engine?
6.
What is the action or the blower drain valve and where is it
located?
7.
How is oil kept trom !lowing into the engine when the engine
is stopped?
a.
What means is provided to change the oil pressure?
9.
Where is the ouno looated 1n a R-1820 engine?
10.
Explain the lubrication or the rooker arms.
11.
Where is the external scavenger line connected?
12.
On
13.
How would you relieve the air in carburetor regulator unit?
14.
Name three oommon reasons tor low oil pressure.
15.
In the event the mixture control ia placed in the idle outotf ROBition and the engine oontinues to operate, what is
the trouble?
16.
What doe,s a coating
plug indicate?
17.
Brietly outline procedure tor removing push rods and rooker
arms?
18.
What ia the correct procedure tor removing the piaton pin
retainer?
what cylinders are p~imer lines oonneoted?
ot
tresh oil on the electrodes ot a spark
�BBSTRICTED
2.0
Page 81
19.
What is the oorreot »rocedure tor piston installation?
20.
How many cylinder hold down cap screws may be satetied
together?
21.
'l'he #5 terminal on the distributor block oonneots to what
cylinder?
22.
Briefly describe the steps tor synchronizing the mags on
the engine.
23.
In case the oil pressure outlet hole in valTe adJusting
screw is lined up with the clamping slot, ia the valve
elearanoe increased or decreased in order to place pressure
hole 3/32" away trom clamping slot?
24.
What is the reason tor adjusting the valves 1n the tiring
sequence?
25.
How is the oil pressure adjusted?
26.
If the spark plug electrodes are heavily coated wiih carbon, what checks should be made to find the cause?
27.
Give briefly the run-in procedure tor an engine when parts
haTe been replaced with pre-run parts.
28.
What type ot cylinder is used on the cowl flap operating.
mechanism?
2g.
Briefly describe the steps for propeller installation.
�a.o
RB8'ltlIC'Dm
Pase
aa
J'LYIJIG l'OBTU88 SQJIOOL
BOBDIG ilROR.dT OOIIPAff
B-lU
9VIPI -
PROQIDURB
am qu,mw
(B-lfB0-11 ul tf)
ROTB:
l.
Baeh ot the station• will be 1D•»e•t•I •• ocm,l~,e4.
Prelimlaary
a.
Open era•• ud reaoTe bold ' town ~01,s.
, •.
o.
4.
•.
t.
Beaove Gil oloth or plT•film ---•
Iaa•all uti-1oer riq.
Reaon ahi:ppiag plq• before turnillg engiJl••
nush out :pickling oil
·
Teat knurled auta oa magneto
tor
g.
Teat rocker box oonr nu,a tor tigh,u•••
h.
Tea, puah roa hou■ iq •lua»• ter
Cheok battle• tor Jr•» gonrnor line hole•
(drill hole• it not 4rille4)
Ch••k battle• tor 1•n•rator ,1aat tu1- hol••
(drill holes it not 4r1lle4)
Inapeot preTioua ten iteu before prooee4inc
tur-.her.
1,
J.
k.
hara•••
tish"••••
('10 ia./lbs.)
tip•••••
HOTJI: The above iteu ean be ,aaa oar• ot while the
engine la •till in the or•t• in th•
of
stanta.
ab•••••
II.
Remove ell81ne tr('Jll era te
··
a. ReaoTe ahippiq i,late · ·
b. · Examine
tor
ia tranait
•. Looaen all pluabiq i,luc• tbat an to be reaoye4
4. Tighten an4 aatety a11 ·»11111b1Da Jlug• to be leti
on engine
•1111••
III.
ReadJua1 priDler diatributor
••
b.
••
IT.
•amac•
••
o.
4.
adiuatiag battle•
Install braoket and olamp on 18 oylinder illtake
pipe (all tour engiaea)
Iaatall bracket an4 olaap on #1 . oylinder intake
:pipe {#1 and l}a engine• only)
AdJuat primer teed 1111• to· olear battle and
eheok roeebu4 line• to ,o» tin oylindera.
Iastallaiion
b.
an«
or
ilr Seal, fixed oowl, •to.
Iaaiall or.-nkoaa• nreather tube
Iaatall cowl support braoket•
Sorape »aini away io make goo4 )on4 tor fixed oowl
Inatall air •••l
�RESTRICTED
v.
Inatallation ot engine 11ounta
a.
b.
o.
4.
••
VI.
4.
e.
f.
g.
- h.
1.
Install supercharger regulator line fittings
Install oil pump line fittings
Install manifold pressure an4 oil pressure
to autosyn transmitter line fitting•
Install external line, propeller governor to
gun synoronizer adapter line
Install primer line (main)
Install anti-icer line
Install propeller feathering pressure line
Install propeller governor pressure switoh tlex
Ue• ·on1y one wittek clamp on high bead fittings
, Accessory-' Installation
a.
b.
c.
4.
••
f.
g.
h.
1.
,•
VIII.
Install dynatoeal "Lord• mount•
Ad.just mounts to pro:per preasure on timkan
tapered roller bearings
Torque Lord bushing bolt• to 175 inoh poun41
Inatal1 tixed cowl and Lord mount to engine
bed to 375 inch pounds
_Install engine bonding straps (tour 1>laoea)
Inatallaticm ot· o11 ·fittings, eto.
a.
b.
c.
VII.
a.o-
Paa•
Install starter and meshing solenoid. Clleok
tor slack. in cable
Install generator
Install fuel pump and fuel pump lines
Install hydraulic pump and ·11nes on B-17E
(#1 engil\e only)
Install vacuum pumps 12 and II engine end lines
Install glycol pump and lin•• (#2 engine and
13 engine· with supplementary heating system)
Bote.:. Glycol pump · should be installed with
writing upside down
Inatall propellet governor and string governor oontrol cables
·
Instali magneto ·blaat tubes
Instal+ generator blast tube and housing around
generator cooling :tan
Instal_l thermocouple and line
Bng~ne Il:lduotion System
a.
b.
o.
.d.
e.
Remove oover from uuluotion caae, waah out with
aolvent and immediately inatall carburetor
Install carburetor shroud
Install fuel pump 'balance line
RemoTe ' blower •drain, dismantle, wash out oil,
grease, . ·eto-. , and: reaasemble it operation is
faulty. :
·
.
Inatall exhaust "Y" cooling blast tube (on
#1 and 1}4, only)
•ns1n••
8'
�BESTBICT.ED
IX.
Bxhauat Kanitold Installation
a.
b.
c.
d.
x.
Install "Y" section first
Adjuat section connecting clam.pa to tree ~o
turn an4 oheok looseness ot bottle
Install left side exhaust stacks going trca
bottom to to:p
Ins~all right side exhaust ataok bottom to top
Magneto Inspection
a.
b.
c.
d.
ll.
a.o
Page
Remove magneto point cover plates, wash out
with Cal4 only
Cheok nagneto timing with engine
Check breaker poiJl't setting to be just opening
#1 oylinder 20~ B.T.D.c. on compression stroke
Install Mag. boost and Jumper tlex
Installation ot mounting rings
Install ring oowl mounting braoketa, rubber
shooks and hoop
b. Install eowl tlap mounting brackete, rubber
shock• and hoop
c • .Adjust cowl tlaps for clearance ot .12 inch
at trailing edge after engine is installed
in place on the nacelle
a.
nz.
At'laehing engine unii to air:plane
a.
b.
c.
d.
e.
t.
g.
Hoist engine unit into place
Torque hangar bolts to 800 to 1200 iJloh pounds
Kake all control rod connections and adjuat
them to allow full traTel {rig cables)
Make all oil, · tuel, glyool, vacuum and hydraulio
line connections at firewall and allow proper
slaok
Fill engine oil tank
Build up hydraulic pressure and bleed hydraulio
line at hydraulic pum.p. (il engine ot B-17E only)
When installing cannon plug line up ridge with
slot don't try to line up prongs.
XIII. Pre-oil Engine
XIV.
General Inspection ot Entire Unit
XV.
-Install Cowling
a.
Allow .12 inoh olearanoe between flap• and
naoell• cowling iJl olosed position.
a~
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_008
Title
A name given to the resource
[Study guides issued by Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Study guides issued by the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. Contains information about engine operation, engine maintenance, and the induction, fuel, and oil systems for the B-17F. 25 typed pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Boeing B-17F Flying Fortress
Training
Extent
The size or duration of the resource.
25 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
documents
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/8c273e52d2f7f1a819fae315055f6bdf.pdf
6c95683fa432056549ede79fbc2748c4
PDF Text
Text
, ,.
-,
./ . ,-,,:
I'
,
RESTRICTED
,
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMP.ANY
B-17F
STUDENT NOTEBOOK
GENERAL
This notebook contains information on the B-17F Flying
Fortress. Included herein are trouble charts, procedure
guides, study guides and supplementary information. All information is subject to the latest technical orders.
INSTRUCTIONS
Study guide questions for the following subjects must be
answered on a separate sheet of paper before attending the
first class in these subjects. The answers must be given to
the instructor in charge of each class.
1.1 Wing, tail and nacelle
1.2 Flight and engine controls
1.5 Landing and tail gear
, 1.4 Fuselage and equipment
1.5 Handling
*4.1 Introduction-n.c. Power
4.2 Equipment Familiarization
4.3 Equipment servicing
4.4 Secondary circuits
4.5 Retraction circuits
4.7 Secondary circuits
2.1 Engine operation
2.3 Induction system
2.5 Fu.el system
5.1
5.2
5.3
5.4
2.5 Oil system
Engine maintenance
(to be turned in at 2.7)
2.a
3.1
3.2
3.3
3.5
Answers may be
the Familiarization
information in this
nical Order will be
Navigational instruments
Flight instruments
Engine instruments
Miscellaneous instruments
Hydraulic system
Oxygen and Anti-icer
Heating and Ventilating
Vacuum and De-icer
found in Technical Order No. Ol-20EF-2 in
Manual--Operation, or in the supplementary
notebook. The index in the back or the Techhelpful in finding answers.
*Before attending electrical class, 4.1, study pages one
thru five in Section 4.0 in this notebook, besides answering
the Study Guide questions.
Bring this notebook and the Technical Order to!!!, classes,
including the Hangar classes.
/
Revised 4/20/43
�RESTRICTED
1.0
Page 1
FLYrnG FORTRESS SCHOOL
BOErnG AIRCRAFT COMPANY
B-17F
STUDY GUIDE QUESTIONS
WING 1 TAIL AND NACELLE-1.l
1.
Give location and brief description of the wing spars.
2.
What disconnections must be made in removing a wing tip?
3.
What are the three main removable parts of the left hand
outer wing panel?
4.
Give four steps in the removal of a wing flap.
5.
How is the anti drag ring retained in position on the
engine'?
6.
Describe briefly the construction and attachment of the
vertical stabilizer.
7.
Why would the elevators and horizontal stabilizers be
removed first in a complete disassembly or the empenage?
�RESTRICTED
1.0
Page 2
FLYmG FORTRESS SCHOOL
BOEmG AIRCRAFT COMPANY
B-17F
STUDY GUIDE SUESTIONS
FLIGHT AND ENGINE CONTROLS-1.2
1.
What sized cable is used for each of the following: ·Engine
controls, main tlight surfaces and servo units?
2.
What are the two uses of turnbuckles and adjusting links?
s.
Where and on what controls are rod and bell crank linkages
used?
4.
Name two of the units comprising the aileron operating
mechanism in the wing.
5.
What kind of mechanism is used to operate each of the trim
tabs?
6.
What two methods may be used to prevent unwinding of cables
from drums during disassembly or remoYal of flight surtaees?
7.
What flight control surfaces can be locked?
a.
After checking on diagrams (Pages 284-289) tell how many
cables run aft through waist compartment?
�RESTRICTED
1.0
Page 3
FLYlliG FORTRESS SCHOOL
BOEmG AilWRAFT COMPANY
B-17F
TROUBLE CHART - FLIGHT AND ENGDIE CONTROLS
TROUBLE
PROBABLE CAUSE
REMEDY
Cable breaks
Rust damage-Broken strands in
cables causing weakness
Never remove Dearborn Nooxide.(In case of breaks
splioe with new cable)
Keep away from Electrical
wiring.
Slack in cables
Safety wires on turnbuckles sometimes are left off allowing them
to unscrew. Cables off of pulleys
due to worn or broken pulleys.
Reapply tension and safety
all turnbuckles. Replace
pulley or pulleys.
Tab and Wing Flap Actu- Lubricant freezes solid
ating struts sometimes
freeze at high altitudes
Lubricate during such conditions with graphite.Too
muoh lubricant.
Uneven operation of con- Uneven tension in cables
trol surfaces.
Apply tension evenly when
rigging and check tension
during inspection periods.
Warp in elevator torque
tubes
Uneven tension in cables-overload
in flight
Adjust cables to even tension.
Flap creeping
Loose linkages-improper setting of
stops-struts out of alignment
Tighten linkages or replace
badly worn parts.Check stops
make adjustment on struts •
.
.
�1.0
RESTRICTED
TROUBLE
Tail wheel will not look
PROBABLE CAUSE
Shear bolt sheared off
Broken look spring
Cable too loose
Rudder and elevators won't Spring in pin broken or has
look
no tension
Fluttering of elevator
trim tab
Tension on cables uneven
hinges or joints worn.
Page 4
REMEDY
Replaoe with shear bolt and
check spring loaded pin.
Replaoe spring
Apply proper cable tension.
Replace spring or readjust
spring tension in pins.
Cheak tension and linkage
of system. Use thumb screw
to tighten wheel.
�RESTRICTF.D
1.0
Page 5
FLYING FORTRESS SCHOOL
BOEiliG AIRCRAFT COMPANY
B-17F
PROCEDURE GUIDE-FLIGHT AND ENGINE CONTROLS
Removal of cables from the flight oontrol system or the
B-17F will involve the removal of at least go% ot the
pulleys. In some brackets the removal of the spacers
only will permit the withdrawal of the swaged terminal
ends. Where the spacers are riveted and the clearance
between the pulley and the spacer does not allow passage
of the terminal, the pulley must be removed.
I.
REMOVAL OF PULLEYS
A.
B.
Points of installation to be observed previous to
pulley removal.
1. Cable alignment
a. A cable which is not correctly aligned with
the pulley has a tendency to wear the side
of the pulley. This may cause the cable to
bind. If this misalignment is not corrected
soon enough it may oause the failure or the
system.
.
b. The misalignment of cables can be corrected
in two ways:
1) The proper spacing of the pulley in the
bracket may 9orrect the fault. This can
be done by adding washers or spacers between the pulley and the bracket.
2) If the ~bove operation is ineffective,
it may be necessary to move the whole
bracket.
2. Pulley spacing
a. The proper spacing of the pulley in the
bracket will prevent the pulley from wearing
on the sides of the bracket or on parts of
the bracket.
b. Pulley spacing affects cable alignment as
noted above.
Care should be taken in removing pulleys to avoid
dropping washers, shims, spacers and bolts into
other operating systems.
II. INSTALLATION OF PULLEYS
A. Spacing
1. Spacing at installation should be equal from
both sides of the bracket.
2. This spacing should be checked by the alignment
of the cable under tension.
3. The angle or the cable pull must be observed.
A oabla making a 90° angle with the pulley
should have a more true alignment than one
making a 45° angle with the pulley.
�0
RESTRICTED
B.
C.
1.0
Page 6
Installation of spacers, washers, etc.
1. Where access is difficult, time can be saved
by using a steel or hardwood plug thru the
pulley bearing for mounting the washers and
spacers. The plug must be cut to the diameter
of the hole thru the pulley bearing. It must
be just :long enough to go thru the pulley bearing -and aooommodate the spacers on each side.
2. The spacers can be stuck onto the ends of the
plug by using a little grease.
3. The cable can then be wrapped around the pulley
in the groove provided ror it.
4. The pulley (with cable installed) can be slipped
into ·the bracket.
5. When the plug thru the pulley bearing lines up
with the bolt hole in the braoket the bolt oan
be installed by pushing out the temporary plug.
INS1'ALLATION OF BOLTS
l. The bolt used must be sufficiently long to go
thru the bracket and allow roam tor a washer
on the threaded end. This washer should seat
in the groove in the end of the bolt. It it
does not the pulley will have a tendenoy to
ride in the groove and this will destroy its
alignment.
.
2. Clevis bolts are provided in increments of 1/16"
It should never be necessary to use more than
two washers with a clevis bolt. On clevis bolts
use onla shear nuts.
3.. Standar .AH bolts are provided in increments of
1/8". The use of two washers with these bolts
is permissible. On standard bolts, use only
castle nuts.
4. A standard cotter pin is used on both AN and
clevis bolts. A look nut may be used if acoess
is difficult. It a tiber look nut must be used
a fillister head bolt is used. This type of
bolt must be satetied with a wire thru the head
or the bolt and thru a hole drilled in the
brr...cket.
�RESTRICTED
FLYING FORTRESS SCHOOL
BOEmG AIRCRAFT COMPANY
1.0
Page_ 7
B-1'1F
JLIGHT AND ENGINE CONTROLS-CABLES
Aileron
160/}+lO#
-
evators
er
Servo
Units
eron
Trim tab
evator
Trim tab
u er
up; right
down• rl
l 8 -7:xlg
0
black
Down
60
50
Trill1 tab
Thrott e
Control
40
40
3
32-7x7
40
32-7x7
40
Up
Down
ght
Lett
Open
Closed
crease
Decrease
n
Cut off
Cold
Hot
20
32-7x7
50
32-7x7
10
Look
Unlock
ook and re ease
reen
�RESTRICTED
1.0
Page 8
FLYING FORTRESS SCHOOL
BOEmG AIRCRAFT COMPANY
:B-17F
STUDY GUIDE-LANDING GEAR 1.3
1.
What tn,e landing gear is used on the B-17 airplane and
what does it consist of?
2.
In removal or the oleo paoking, what procedure would
you follow if it stuok?
3.
If the oleo is los-ing pressure, what would be the probable cause and what precaution would you take in making
ths necessary repair?
4.
List ·the pre catt, ions that should be observe,d when installing the brake return boost valve?
5.
List the oleo and tire inflations tor both the main landing gear and tail gear of the B-17F.
6.
What is the purpose of the neoprene bumpers and where are
they located?
7.
Where is the anti-shimmey brake located and how should it
be serviced?
a.
What is the shear bolt used for and where is it located?
9.
What is the purpose of the torsion links and what precaution . should be observed when disconnecting them?
10. EXJ:)lain the procedure to follow when removing a tire?
�RESTRICTED
1.0
Page 9
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
TROUBLE CHART - LANDING GEAR AND TAIL GEAR
TROUBLE
Oleo - Loss of oil and air
pressure landing gear or
tail gear
Landing gear or tail gear
creeping
PROBABLE CAUSE
REMEDY
Valve body loose - valve core
worn gasket behind valve body
compressed.
Replace valve core or valve
body gasket
Lea-king around oleo packing
Remove oleo from housing and
check packing-excessive leakage, replace packing if small
amount or leakage is apparent
tighten packing nut 1/2 turn.
Neoprene bumpers worn excessive- Replace neoprene bumpers
ly.
Limit switches improperly set
eheok limit switch setting
Retracting screw and/or nut worn Replace screw and/or nut
Landing gear or tail gear, Excessive grease on retracting
lowering and retracting
screw becoming frozen
slowly or landing gear
frozen (failing to operate)
Slippage of clutch assembly.
Remove exc&ssive grease from
lower end of retracting screw
housing.
Check clutch assembly
Retracting gear motor brushes
worn causing motor to "drag".
Replace worn brushes in motor.
Binding of retract nut and retract screw
Check retracting screw and nut
�RESTRICTED
TROUBLE
PROBABLE CAUSE
REMEDY
1.0
Page 10
Bolts shearing off or bending Excessive loading conditions
at connection of drag strut
caused by rough landings and
to drag strut support.
take-offs.
ReJ>lace 5/8" bolts with
3/4" bolts on B-17E. Drill
holes to suit 3/4" bolt.
Excessive torque or "whip·:ping action" in wheel and·
axle. "Hammering effect"
noticed in knuckle joint.
Ball thrust bearings at knuckle
joint of torsion link worn and/
or connecting bolt improperly
tightened.
Replace bearings if worn.
Check and maintain proper
freedom of movement of bolt.
Bolt should rotate with medium pressure of hand.
Brake dragging and over heating.
Expander tube grown excessively
Expander tube should be
checked. Replace if necessary
lml>roper clearance between
brake blocks and drums
Check 0learance between brake
block and drum and replace
brake block
·
Retaining spring broken
Replace broken springs
Hydraulic pressure failure
Check hydraulic pressure.
Check tor proper clearances
before removal
Brake blocks worn excessively
It brake ~ooks are worn
more than 1/16" replace
with new blooka
Block retaining 'Spring broken
Check tor brokea retaiaing
s~ring-replace ~t broken.
lml>roper clearances
Replace brake blooks
Brakes refusing to hold
properly
C)
�RESTRICTED
TROUBLE
Excessive wear- in bronze
collar on oleo housing
Excessive Tibration set up
in tail
PROBA.BLK CAUSE
lm_proper lubrication
Cheak grease titting aa4 lubricate properly
Excessive grit and dirt
collecting on oleo cylinder
and mixing with grease to
form an abrasive.
Keep oleo cylinder wiped clean.
Anti-shimmy brake not funotioning correctly.
b. Linings slick with dirt
and grease
c. Improper torque applies
a. Replace it worn down to rivet
heads.
b. Clean brake surface & brake
11n1ns.
c. A~I>lY 4,20 inch/lbs. ot torque
to assembly
d. Replace spring
Spring broken or weak
Check spring
a. Linings worn excessively
anti-shimmy brake
d. Failure of compression
spring
Tail wheel spindle fails
to lock properly.
REMEDY
1.0
Page 11
Lock pin binding or dragging Check lock pin for proi•r aeaiing
with look :plate.
Locking lever, control cable ~ork locking l•T~~ 1a ooolcpit to
and pulleys improperly tune- check pulley and cable movement.
tioning.
Shear bolt sheared ott
Replace shear bolt with 88.JD.e type
bolt
Cracks noticeable in hub
Fatigue failure due to con- Replace wheel
and/or rim ot tail wheel and centrated stresses at abrupt
landing .gear wheel.
section changes
�1.0
Page 12
RESTRICTED
TROUBLE
Landing gear warning horn
blows or landing gear position lights flicker when
airplane is taxied or when
the engines are run on the
ground.
PROBABLE CAUSE
REMEDY
Landing gear not looking in
down :position
Check limit switch setting
and neoprene bumpers for wear
Tail gear not looking in
down position
Check limit switch setting
and neoprene bumpers for wear
Short in wiring which makes
contacts when airplane is
vibrating.
Check wiring.
�1.0
Page 13
RESTRICTED
FLYmG FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-1'7F
STUDY GUIDE QUESTIONS
FUSELAGE AND EQ.UIP.MENT 1.4
or
1.
What type construction is the fuselage
the B-17?
2.
Explain how to install a lite rart.
s.
What are some or the things the band tire extinguishers
are checked tor.
4.
Name and give location or each compartment ot the airplane.
5.
Explain the d.itteren.t actions that take place when the
emergency bomb release is operated
�RESTRICTED
1.0
Page 14
FLYING FORTRESS SCHOOL
BOElliG AIRCRAFT COMPANY
B-17F
TROUBLE CHART-FUSELAGE AND EQUIPMENT
TROUBLE
PROBABLE CAUSE
REMEDY
A. Craoks in metal covering
Corrosion-scratch adverse flying
condition
Replace with patoh.
B. Dents in skin
Adverse flying condition
Iron out
c.
Adverse flying condition
Repair
Bent structural members
D. Broken structural members Adverse flying condition
Re:plaoe
Adverse flying condition
Replace
A. Plugged nozzel
Dirt
Clean
B. No charge in bottle
Used and not replaced. Bottle
damaged, not inspected
Replace ~i th new
extinguisher
c.
Misused - shot.
Replace or repair
E. Loose rivets
HAND FIRE EXTilJGUISHER
Broken Bracket
D. Bent or broken extinguish-Shot - adverse flying condition
er
Replace with new bottle.
�RESTRICTED
TROUBLE
PROBABLE CAUSE
1.0
Page 15
REMEDY
- LIFE RAFT
A. Fails to eject rrom
compartment
Rolled improperly-Release cable
installed improperly.
Roll correctly. Propar
slack in cable
B. Fails to inflate
Release cable not hooked properly - valve stuck. Hole in bladder
no pressure in CO2 bottle
Hook cable to release
mechanism. Examine valve
cone. Examine bladder for
holes. Replace bottle.
c.
~oor improperly latched. Bent rod
and hooks
Be very earetul in shutting and hooking compartment door. Striaghten rod
and hooks.
A. Hinges bent or broken
Door check not working. Shot.
Replace check.
B. Retracting screws damaged
Shot or adverse weather
Replace
c.
Landing with doors open - adverse
!lying condition.
Repair or replace.
Comes out in flight
BCl4B DOORS
Doors bent or broken
�BESTRICTED
1.0_
Page 16
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMP.ANY
B-17F
STUDY GUIDE-HANDLING 1.5
1.
2.
What is the main function of the nacelle jack?
When hoisting the entire plane what preoaution must
be observed?
3.
How would you handle the tail gunners compartment when
hoisting?
4.
Explain in detail by describing the hoist fittings how
you would remove the outboard panel.
5.
List the number, looation, and allowable load tor each
jacking cone.
6.
Why should the parking brakes be released betore jack-
7.
I t damage has caused the airplane to rest considerably
s.
List all the precautions that should be obserTed in
jacking.
9.
List reasons tor using caution in the operation of the
brakes in low temperatures.
ing up the airplane?
ott the lateral position, what procedure may be followed
to expedite the jacking operation?
10. Should the notches in the control quadrants of the rudder and eleTator be lubricated, and if so what lubricant
should be used?
�RESTRICTED
1.0
Page 17
JI'
FLYING FORTRESS SCHOOL
BOEING AIRCRAFT COMPANY
B-17F
SUPPLEMENTARY rnFORMATION-STRUCTURAL REPAIR 1.7
Read this information and answer the Study Guide ~uestions on
Page 22 before attending class.
Before making structural repairs on the B-17 refer to T.O. Ol~20E-3
RIVETS:
Most of the rivets used on the B-l?F are made of Al7ST
alloy and are identiried by a dimple in the center of the head.
The Al7ST rivets are only about 75% as strong as the 24ST
rivets used around the spars and in places where the maximum
strength is necessary. The disadvantage in using 24ST rivets
is that prior to driving they must be heat treated and kept on
dry ice which keeps them soft, hence the name "ice box rivets."
24ST rivets start hardening upon reaching roam temperature, .so
must be driven immediately after removal from the ice box. 24ST
rivets are identified .by two elevated dashes on the head.
Monel rivets a.re used to rivet stainless steels.
a plain head.
These have
SELF-UPSETTmG RIVETS
Self-upsetting rivets (blind) are used where it is difficult
to buck the opposite side. These are used in only a few places
in manufacture due to the cost and inferior strength. However .,
they are used to a greater extent in combat zones because they
are easier to drive in inaccessable spots.
,_ _•--o~.-:~=:,....
\
A Rivnut has a weak spot that bulges when
a tool is pulled up through the center.
STRENGTH OF RIVETED cTOlliTS
Rivets should never be used in tension (a pull lengthwise
to the rivet.) The head would pry off easily. This type of load
should be carried by a bolt and nut. (Figure A)
4
FIGURE
A
FIGURE
e.
FIGURE C
FIGUR.E 0
�RESTRICTED
1.0
Page 18
Rivets have good shear strength (Fig. B)
shear failure one of threa things would occur:
(1)
In
case
of
The rivet would shear in half.
(2) The rivet would shear the sheet cutting through . the
margin. This. is caused by the rivet being too close to the edge.
(Figure C)
by
(3) The metal would fail between rivets.
rivets being too close together. {Figure D)
This is oaus,ed
I
Therefore, the above should be balanced to where , the edge
margin is equal to the shear value in addition to keeping sufficient metal between rivets. The most common error of a mechanic is to place a rivet too close to the edge.
EDGE MARGIN
Edge margin is the distance from the center of the rivet
to the edge of material with a 1/4" minimum. This should be
approximately twice the diameter of the rivet depending upon
the gage or the sheet.
Rivet spacing varies from three times the diameter of the
rivet to twenty-four times the thickness of the sheet being used.
Copy spacing after like places on the airplane. If this
is not possible, a good formula to follow is about five times
the diameter of rivet. The manufactured head should be next
to the thinnest sheet whenever possible.
DEFECTIVE RIVETilrG
Make sure the tools and rivets are right before starting.
job can be ruined by a single slip. If in doubt try out a
few rivets in a piece of scrap.
A
Use tools that leave no marks on the work.
Use the proper size rivet die or the manufactured h~ad
will be marred.
If the rivets are too long, -the rivet will tend to bend
before it is upset. The rivet should protrude through the material
one and a half times the diameter of the rivet.
�RESTRICTED
1.0
Page 19
EXAMPLES OF WEAK RIVETS
The upset head (the peened end of the rivet) is
driven over to one side and is oblong.
The upset head is over driven. This rivet is overworked and brittle and may cause a crack in the head.
The upsetting bar or set was not held at 90° to the
work.
The upsetting bar or set was held half off of the
upset head.
Rivet not driven hard enough. Light blows caused
the end of the metal to harden and funnel out.
I c:::::
Rivet spreading between sheets. If draw tool
doesn't make sheets stay together, drive only
enough to swell rivet in the hole then use an
oversize draw tool.
Rivet not drawn up tight.
Hole not straight.
Remove and drili straight.
Rivet die not held at 90° to work causing a damaged
sheet.
Wrong rivet die.
Over driven or rivets too large for thickness.
�RESTRICTED
1.0
Page 20
RIVETING TOOLS AND SHOP PRACTICE
The job of riveting is a particular one especially in
tight places which often require special tools. Angle drills
or extension drills are sometimes necessary. With these, remember to have a firm hold and to drill slowly by turning the
switch off and on. It is often a good idea to wrap tape
around the drill to act as · a bumper. Thi.s would prevent injuring something inside the ship such as the bulb of a longitudinal stiffener angle, tubing, cable, etc.
Holes and sheets should be burred before assembling so
sheets will lay flat and won't scratch each other during assembling. Burrs should be cleaned from between sheets with a hook
made from a hack saw.
Clecos are sp_ring clamps used to hold sheets together and
used instead of nuts and bolts.
When riveting a large sheet, start from the center and
work out, riveting about every fourth rivet, after the sheet
~s "tacked" in this manner, rivet throughout.
This works the buckles out toward the edge.
When putting a piece of skin over the framework a "shock
cord" (an elastic rubber cord) should be stretched over the metal
skin drawing it tight before drilling.
Bucking bars, draw tools and gun dies should be kept polished on every surface that might come in contact with rivets or
metal.
Any hammering on them would necessitate a long and tedious
job of sanding them down again.
If a rivet die were hit against steel it would deform its
shape so the rivet head would not fit. In this case, put the
die in a drill press and sand to the shape of the rivet head.
To take out rivets be careful not to ruin the sheet metal.
First start the drill by hand, this cuts a deep enough centerpunch to prevent the drill from sliding off the rivet. Watch
the drill carefully and push toward the center. The head may
be picked off with a pin punch and the old rivet driven out.
If a steel backing ~lock is used, be sure it is taped to
avoid marks on the under side.
�,.
RESTRICTED
1.0
Page 21
INFORMATION TABLES
Rivet Holes
Bolt Holes
Drill Size
Smooth Fit
Drill Size
Loose Fit
10-32
#11
1/4-28
5/16-24
Drili
Rivet
Size
Size
t,a
1/16
/j51
1/4
#F
3/32
#40
1/0
#V
21/64"
1/8
#30
25/64"
5/32
/J20
7/lf?-20
29/64"
3/16
/110
1/2 -20
33/64"
1/4
#F
5/16
l}o
3/8
1/V
Bolt
Size
3/8 -24
Rivet Heads
Rivet Materials C_
ode
(24ST,
DD
alloys(l7ST
D
(Al7ST AD
Pure alum.-2S (No mat.
code letters
AN 430, Round
AN 425, ?8° Countersunk
AN 442, Flat
AN 456, Brazier
BAG 1345, Skin
Aluminum
Copper
M.onel
Composition Chart
Rivet Identification
ANl
4
[-DLD-[-iDiameter in 32nds
Length in 16ths
Material Code
Type of head
Army and Navy standard
C
SS
Code
Tempers. Copper Manganese Mag.
17S
Al7S
0-T-RT
T
2S
O¼ H to H.O
245' 0-T-RT
4.5
4.
2.5
1.5
.5
0
O
.6
.5
.3
0
�...
RESTRICTED
1.0
Page 22
INSIDE BEND RADII FOR
SHEET METAL
GAGE
-24SO
24ST
.016
.020
.025
.063
.063
.063
.063
.063
~032
(\~~
.040
.051
.064
.072
• 094
.094
~
.125
. • 188
.219
.135
.156
e08l
.091
.281
.l.88
.344
.375
.438
.531
.656
.188
.219
.250
.395
.500
.102
.125
.,156
.188
1..P.~ .
.156
· .781
STUDY GUIDE - STRUCTURAL. REPAIR 1.7
'
1.
When would a monel rivet be used instead
o-r an Al. 76T and how are they iden t -it'ied?
2.
Define "edge margin". What would the edge
margin be ror a 3/32 Al?ST rivet?
3.
Under what conditions woul.d angle or extension drills be used?
4.
Ex:plain the :procedure tor removing a rivet.
5.
How
6.
Where are 24ST rivets used?
ould an Al7ST rivet be identified?
•
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_007
Title
A name given to the resource
[Student notebook issued by Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Student notebook issued by the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. Contains information about the B-17F, including study guide questions and trouble charts. 23 typed pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Boeing B-17F Flying Fortress
Training
Extent
The size or duration of the resource.
23 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
notebooks
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/ff7eafa3479b3086fc99fcd73ed9bec8.JPG
8cbef8b8bce1c8dc7c101c0dffb14a3b
https://digitalcollections.museumofflight.org/files/original/bee2545d62eb4264aaf69bc654585d1f.JPG
9d463ece4908c846222bf3f1068cc5b7
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_006_01
2018-00-00-130_text_006_02
Title
A name given to the resource
[Student application form for Boeing Flying Fortress School]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Student application form for the Boeing Flying Fortress School in Seattle, Washington, circa 1940s. Two pages.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Training
Extent
The size or duration of the resource.
2 pages ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
forms (documents)
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/caac097cc66ff24f4ae6ccda943d465f.JPG
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Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_005_01
2018-00-00-130_text_005_02
2018-00-00-130_text_005_03
2018-00-00-130_text_005_04
2018-00-00-130_text_005_05
Title
A name given to the resource
Flying Fortress School / Introductory pamphlet / Student regulations
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
United States. Army. Air Corps
Description
An account of the resource
<p>Pamphlet issued to incoming students of the Boeing Flying Fortress School, Seattle, Washington, circa 1940s. Contains the following sections: Introduction -- Secrecy -- Material for study -- Study Hall -- Grades -- Badges Airplane in general -- Entering and leaving buildings -- Lost and found articles -- Time schedule -- Questions & correspondence -- Regulations.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circa
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
United States. Army. Air Corps
Training
Extent
The size or duration of the resource.
1 pamphlet (5 pages) ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
pamphlets
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
Copyright undetermined
-
https://digitalcollections.museumofflight.org/files/original/223a253e21be6145a6aeb825468855b9.JPG
449f609673be13f1b071fca8fc352d70
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_004_01
Title
A name given to the resource
[Memorandum to students and instructors of Boeing B-17 Flying Fortress School, July 2, 1943]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Memorandum to students and instructors of the Boeing B-17 Flying Fortress School, July 2, 1943. Contains new code numbers for subjects taught at the school. One typed page.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1943-07-02
Subject
The topic of the resource
World War, 1939-1945
Boeing Company
Boeing (B-17) Flying Fortress School
Training
Extent
The size or duration of the resource.
1 page ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
memorandums
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright
-
https://digitalcollections.museumofflight.org/files/original/aee4eb8c10741483ed0be4f5ff4e13a4.JPG
27d8e56872c7127fb1722845d5c5d7f3
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Dan Perkins Collection of B-17F Training Materials
Description
An account of the resource
<p>The <strong>Dan Perkins Collection of B-17F Training Materials</strong> consists of documents and training materials related to B-17s. It includes: a travel itinerary for a Boeing Company engineer dated August 31, 1943; Boeing Aircraft Company internal memo from Chief Engineer W. E. Beall asking for donations for War Chest Drive, October 10, 1942; copies of Boeing Aircraft Company letterhead; and B-17F Training materials from the Boeing Flying Fortress School, version dated April 20, 1943.</p>
<p>The B-17 training materials are comprised of: 1. Flying Fortress School Introductory Pamphlet: Student Regulations 2. Flying Fortress School Form 3. Memo: New Subject Code Index Numbers 4. Flying Fortress School, Boeing Aircraft Company B-17F "Student Notebook" 5. Flying Fortress School, Boeing Aircraft Company B-17F "Inspections" 6. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide Questions, Wing, Tail and Nacelle - 1.1" (2 copies) 7. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Information - Structural Repair 1.7" 8. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide-Engine Operations 2.1" 9. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Questions 3.1" 10. Flying Fortress School, Boeing Aircraft Company B-17F "Supplementary Electrical Information - 4.1: Facts to be considered in the Operation of a Reverse Current Relay" 11. Flying Fortress School, Boeing Aircraft Company B-17F "Study Guide - Instruments 5.0"</p>
<p><strong>Digitized Materials:</strong> This collection has been digitized in its entirety.</p>
<p>Please note that materials on TMOF: Digital Collections are presented as historical objects and are unaltered and uncensored. See our <a href="https://digitalcollections.museumofflight.org/disclaimers-policies">Disclaimers and Policies</a> page for more information.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-1943
Creator
An entity primarily responsible for making the resource
Perkins, Dan
Source
A related resource from which the described resource is derived
<a href="https://archives.museumofflight.org/repositories/2/resources/332">Guide to the Dan Perkins Collection of B-17F Training Materials</a>
Language
A language of the resource
All materials are in English.
Rights Holder
A person or organization owning or managing rights over the resource.
The Museum of Flight Archives
Rights
Information about rights held in and over the resource
Permission to publish material from the Dan Perkins Collection of B-17F Training Materials must be obtained from The Museum of Flight Archives.
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130
Text
A resource consisting primarily of words for reading. Examples include books, letters, dissertations, poems, newspapers, articles, archives of mailing lists. Note that facsimiles or images of texts are still of the genre Text.
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
2018-00-00-130_text_003_01
Title
A name given to the resource
[Boeing Aircraft Company stationery]
Source
A related resource from which the described resource is derived
The Dan Perkins Collection of B-17F Training Materials (2018-00-00-130), Folder 1
Creator
An entity primarily responsible for making the resource
Boeing Company
Description
An account of the resource
<p>Blank piece of stationery with Boeing Aircraft Company letterhead, circa 1940s.</p>
Date
A point or period of time associated with an event in the lifecycle of the resource
1940s circe
Subject
The topic of the resource
Boeing Company
Extent
The size or duration of the resource.
1 page ; 8.5 x 11 in
Language
A language of the resource
English
Format
The file format, physical medium, or dimensions of the resource
stationery
Bibliographic Citation
A bibliographic reference for the resource. Recommended practice is to include sufficient bibliographic detail to identify the resource as unambiguously as possible.
The Dan Perkins Collection of B-17F Training Materials/The Museum of Flight
Rights
Information about rights held in and over the resource
In copyright