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2002
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ATP Grid Index to Manufacturer’s Publications:
Beech Aircraft Corp.
55, A55, 855, C55, D55, E55, and 58
Baron Model
Shop Manual
Section
General
Topic
Information
Title Page
List of
Chapters (Table
of Contents)
Record of Revisions
Temporary Revisions
of Transmital (Hightlights Of Changes)
Record of
Letter
List of Effective Pages
Index
Alphabetical
01
General
Information
Information
General
Powerplant
Miscellaneous
Service
Supplementary
02
Publications
Ground Handling And Servicing
Ground Handling
Servicing
03
Airframe
Airframe
Wing
Fuselage
Seats
Cabin Doors Latching
Adjustment
Utility Baggage Door
Interior Door Handle
02/23/2001
Copyright
Aircraft Technical Publishers
BC
0425
MM 1
Page
1
of
4
Section
Topic
Cargo
Door
Windows
Fiberglass
04
Flight Controls And Surfaces
Flight Controls
Aileron System
Elevator System
Electric Trim Tab System (Optional)
Rudder And Tab
Vertical Stabilizer
Horizontal Stabilizer
Balancing Control Surfaces
Flaps
05
Landing Gear And Brake System
Brake System
Landing Gear System
06
Power Plant
Power Plant
07
Propeller
Propeller
Troubleshooting Propeller Synchronizer
08
Fuel System
Fuel System
Applicable
To Beechcraft Barons)
09
Pressurization (Not
10
Heating And Cooling System
Heating and Ventilation (TC-1 thru TC-1657,
TE-1 thru TE-967
(Except TE-959)
TH-1 thru TH-436)
Heating and Ventilation (TC-1 thru TC-1657,
TE-1 thru TE-967
(Except TE-959)
TH-1 thru TH-436)
Heating and Ventilation (TC-1 thru TC-1657,
TE-1 thru TE-967
(Except TE-959)
TH-1 thru TH-436)
Heating and Ventilation (TC-1 thru TC-1657,
TH-1 thru TH-436)
TE-1 thru TE-967 (Except TE-959)
After
Ventilation (TC-1658
After, TE-968
Heating
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Aircraft Technical Publishers
BC
0425
MM
Page
2
of
4
I
Section
and TH-437 and After)
Heating
Ventilation (TC-1658
After, TE-968
After
After, TE-968
After
and TH-437 and After)
Heating
Ventilation (TC-1658
and TH-437 and After)
TE-968 and After; TH-347 and After)
After: TE-959;
Troubleshooting Heater System TC-1658
Precautionary Service Measures
Troubleshooting Air Conditioning System
TE-1119, TE-1125 And After; TH-873, TH-895
11
After
Utility System
Oxygen System
Vacuum System
Surface Deicer system
Stall Warning System Adjustment
Anti-Icing Systems
Propeller Deicing
H-14 Autopilot System
Autopilot Troubleshooting Guide
Electric
12
Aircraft Finishes
Airplane Finish
13
Care
Electrical System
Electrical System
Alternator System
Starter
Electrical Utilization Load Chart (Std
Light
Bulb
Replacement
Equipment)
Guide
Electrical System
Troubleshooting Batteries
Grimes Stobe Light System
Emergency Location Transmitter
14
Wiring Diagrams
Wiring Diagrams
15
Overhaul And
Replacement
Schedule
Time Limits/Maintenance Checks
Overhaul and
02/23/2001
Replacement Schedule
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Aircraft Technical Publishers
BC
0425
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Page
3
of
4
Section
Topic
16
Periodic
Inspections
Scheduled Maintenance Checks
100-Hour
Electric
Inspection
Propeller Deicer System
End of Index
02/23/2001
Copyright
Aircraft Technical Publishers
BC
0425
MM)
Page
4
of
4
NI FGI
INTRO
Raytheon Aircraft
Beech
Baron,
55
TC-1 thru TC-190
A55
TC-191 thru TC-349
TC-351 thru TC-370
TC-372 thru TC-501
B55
TC-371,TC-502 and After
C55
TC-350, TE-1 thru TE-451
D55
TE-452 thru TE-767
E55
TE-768 and After
58
TH-1 and After
Shop
Manual
NOTE
This manual
was
formerly called the
Copyright 0 Raytheon
August 20,
Aircraft
Company
Shop
Manual.
2000
P/N 55-590000-13E18
P/N 55-590000-13E
Reissued:
Beechcraft Baron
1978
Revised: November 10, 2000
Published
By
RAYTHEON AIRCRAFT COMPANY
P.O. Box 85
Wichita, Kansas 67201
U,S.A
NOTE
Where Beech Aircraft
Corporation is referred to in this publication,
Raytheon Aircraft Company.
it will be taken to read
EXPORT STATEMENT
Exported under the authority of license exception: TSU.
"These commodities, technology or software were exported from the United
States in accordance with Export Administration Regulations.
Diversion contrary to U.S. law prohibited.
payMmon
Raytheon
Member of GAMA
Aircraft
Company
General Aviation
GA~HA
Manufacturers Association
RECORD OF REVISIONS
MFG REV
DESCRIPTION
NO
List of Effective
see
E16
See List of Effective
E17
E18
8/15/95
Pages
E15
ISSUEDATE
Pages
SEE LLST OF EFFECTIVE: PAGES
SEE LLST OF EFFECTIVE
4/02/99
10/28/99
ATPREVDA
11/17/97
06/28/99
2/07/00
INSERTED BY
ATP/RLL
ATP/BP
ATP/JB
RECORD OF TEMPORARY REVISIONS
ATP REV
INSERT
DATE
REV
REMOVE
ISSUE DATE
DATE
BY
REMOVED
INCOR
BY
3/8/97
11/17/97
ATP/RLL
TEMP
REV NO
4-1
15-1
DESCRIPTION
Section 4 pgs 4-2 8 4-6
ON 15
15-2
1
1
2/9/98
06/28/99
1~
E16
~I
ATP
a
Aircraft
BEECH BARON 55 AND 58 MAINTENANCE MANUAL
RECORD OF TEMPORARY REVISIONS
Removed
Inserted
Affected
Temporary
Revision
No.
When
of the
y
Chapter
Page(s)
By
Date
evision
No.
Date
inserting or removing a temporary revision, the applicable rev/sionnumber and the initials
person(s) inserting and/or removing these revisions should be recorded on these pages.
NOTE: Insert the Record of
Temporary
Revisions after the
Log of Temporary Revisions page(s).
Page
Aircraft
BEEC~ BARON 55 AND 58 MAINTENANCE MANUAL
RECORD OF TEMPORARY REVISIONS
Removed
Inserted
Affected
emporary
Revision
No.
Page
2
evlslon
Chapter
Page(s)
By
Date
No.
Date
Ail´•oraft
BEECH BARON 55 AND 58 SHOP MANUAL
LOG OF TEMPORARY REVISIONS
Revision
No.
Revision
Revision
Subject
Date
4-1
Mar 8/96
4-2
Nov 15/93
15-1
Oct 31/97
Incorporated
Control Column Arm and Dual Control Arm Removal and Installation
E16
Flap Drive Cable ConnectionProcedures
Overhaul and Replacement Schedule Landing Gear
E16
E16
Page 1
Apr 2/99
NOTE: Insert this
Log
of
Temporary Revisions
after the Record of Revisions page.
Rayl~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
P/N 55-590000-13E, REVISION
The sections which have been revised
or
added
are
E18, November 10, 2000
listed below with the
highlights
of each
change.
Remove the
affected pages and insert the El 8 revision in accordance with the attached Instruction Page. Enter the revision number and the date inserted on the Record of Revisions page of this manual. The Highlight Page may be retained with
the manual for future reference.
HIGHLIGHTS
Description
Chapter/Section
Section 1
Added
correct
of
Change
warning to identify each side of a component being disconnected to facilitate
reassembly. Added an overhaul manual for electric boost pumps under Supplier
a
Publications.
Section 3
Added Forward
Carry-Through Spar
Cover Removal and Installation
procedures.
inspect the wing bolts by magnetic particle process before
installation. The wing bolt mounting nuts must be replaced at each inspection interval.
Revised
Wing
Installation to
Pagel
E18
Nov 10/00
REVISION 55-590000-13E18
to the
BEECH BARON 55 AND 58 SHOP MANUAL,
C
P/N 55-590000-13E
(Reissued: August 20, 1978)
REMOVE
CHAPTEW
INSERT
CHAPTER/
PAGE
SECTION
PAGE
SECTION
Title
Page
Logo Page
A
B
Page
Page
ALL
Title
Page~
Logo Page
List of Effective
List of Effective
Pages
Pages
A
B
1
Page
Page
1-1
DATED
Nov 10/00
Cist of Effective Pages
E18
List of Effective
El 8
Pages
1
thru 1-30
ALL
3
3-1
5
thru 3-57
NOTE
These instruction pages may be discarded after the above revision has been
properly incorporated into the Beech Baron 55 and 58 Shop Manual
Page
1 of 1
El 8
E-l 8
E-18
E-18
Raytheon Aircraft
BEECH BARON 55 AND 58
SHOP MANUAL
LIST OF EFFECTIVE PAGES
Always destroy superseded
pages when you insert revised pages.
E Reissue
Aug 20,
El Revision
Jan 18, 1980
E2 Revision
Feb 29, 1980
E3 Revision
Jul 18, 1980
E4 Revision
Apr 6,
1981
E5 Revision
Nov 25, 1981
E6 Revision
Jun 6, 1982
E7 Revision
Jun 6, 1983
E8 Revision
Oct 14, 1983
E9 Revision
Jul 19, 1984
E10 Revision
May 29,
1985
Ell Revision
Jul 25, 1985
E12 Revision
Mar 27, 1987
E13 Revision
Mar 30, 1990
E14 Revision
Dec 20, 1991
E15 Revision
Aug 18,
1995
E16 Revision
Apr 2,
1999
E17 Revision
Oct 28, 1999
E18 Revision
Nov 10, 2000
NOTE: A List of Effective pages will be in the front of each
ic
1978
chapter.
are assigned a part number which appears on the title page with the date of the issue. Subsequent revisions are identified by the addition of a
code after the part number. Al after a part number denotes the first revision to the basic publication, A2 the second, etc. Occasionally, it is necessary to
reissue and reprint a publication for the purpose of obsoleting a previous issue and outstanding revisions thereto. As these replacement reissues are
the code will also change to the next successive letter of the alphabet at each issues. For example, B for the first reissue, C for the second, etc.
publications
ordering a handbook, give the basic number, and the reissue code when applicable, if a complete up-to-date publication
be required, give the basic number and revision code for the particular set of revision pages you desire.
is desired. Should
only revision
E18
Raytheon Aircraft
BEECH BARON 55 AND 58
SHOP MANUAL
LIST OF EFFECTIVE PAGES
Always destroy superseded
(Continued)
pages when you insert revised pages.
LIST OF EFFECTIVE PAGES
Title
Page
E18
Nov 10, 2000
Logo Page
E10
May 29,
8-20 thru 8-24
Original
1985
Page
E18
9-1
Original
BPage
E18
10-1 thru 10-9
Original
i thru xliii
E17
Oct 28, 1999
10-10 thru 10-11
El
Jan 18, 1980
1-1 thru 1-30
El 8
Nov 10, 2000
10-12 thru 10-24
E15
Aug 18,
1995
2-1 thru 2-2F
E15
Aug 18,
1995
11-1 thru 11-14
E10
May 29,
1985
2-3 thru 2-6C
E15
Aug 18,
1995
11-15 thru 11-88
E15
Aug 18,
1995
2-7 thru 2-12A
Ell
Jul 25,1985
12-1 thru 12-9
E3
Jul 18, 1980
2-13
E8
Oct 14, 1983
13-1 thru 13-11
Original
13-12 thru 13-12D
A
2-14
Original
E9
Jul 19, 1984
Original
2-15 thru 2-18
E8
Oct 14, 1983
13-13 thru 13-18
2-19 thru 2-20A
E15
Aug 18,
1995
13-19 thru 13-72
Ell
Jul 25,1985
2-21 thru 2-23
E8
Oct 14, 1983
13-73 thru 13-77
E12
Mar 27, 1987
i-24
E10
May 29,
14-1 thru 14-51
2-25 thru 2-31
E8
Oct 14, 1983
14-52
3-1 thru 3-57
E18
Nov 10, 2000
14-53 thru 14-69
4-1 thru 4-85
E16
Apr 2,
14-70 thru 14-72
5-1 thru 5-86
E17
Oct 28, 1999
14-73 thru 14-131
6-1 thru 6-26
E15
Aug 18,
14-132 thru 14-135
7-1 thru 7-9
E16
Apr 2,
8-1 thru 8-17
8-18
E18
8-18A thru 8-19
E3
1985
1999
1995
1999
Original
El
Jan 18, 1980
Original
E15
Aug 18,
1995
Original
E5
Nov 25, 1981
Original
14-136 thru 14-169
1999
Original
15-1 thru 15-5
E16
Apr 2,
Jul 18, 1980
16-1 thru 16-18
E17
Oct 28, 1999
Raytheon
Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TABLE OF CONTENTS
General Information
SECTION 1
SECTION 2
Handling
Ground
and
Airframe
SECTION 3
SECTION 4
SECTION 5
Flight
Landing
Controls and Surfaces
Gear and Brake
System
SECTION 6
Power Plant
SECTION 7
Propeller
Fuel
SECTION 8
System
Pressurization
SECTION 9
SECTION 16
Heating and Cooling System
SECTION 11
Utility Systems
SECTION 12
Aircraft Finishes
Electrical
SECTION 13
SECTION 15
SECTION 16
System
Wiring Diagrams
SECTION 14
E17
Servicing
Overhaul and
Replacement Schedule
Periodic
Inspections
ALPHABETICAL
INDEX
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Name
Section
Section Name
Page
Access
Openings, Fuselage (Model 55’s)
Airframe
3
4
Access
Openings, Fuselage (Model 58)
Airframe
3
5
Access
Openings, Wing (Model 55’s)
Airframe
3
6
Access
Openings, Wing (Model 58)
Airframe
3
7
Accumulator, Propeller
Propeller
7
8
Accumulators, Propeller Unfeathering
Ground
2
9
Actuator, Aileron Trim Tab
Flight
4
16
5
78
6
3
Actuator
Assembly, Landing Gear
Handling
and
Servicing
Controls and Surfaces
Landing
Gear and Brake
System
Actuator, Cowl Flap
Power Plant
Actuator, Elevator Trim Tab
Flight
Controls and Surfaces
4
35
Actuator, Elevator Trim Tab-Electric
Flight
Controls and Surfaces
4
46
Actuator, Flap
Flight
Controls and Surfaces
4
83, 84
5
78
Actuator Overhaul,
Landing
Gear
Landing
Gear and Brake
System
Actuator, Rudder Trim Tab
Flight
Controls and Surfaces
4
56
Balancing
Flight
Controls and Surfaces
4
61
Flight
Controls and Surfaces
4
15
Aileron Installation
Flight
Controls and Surfaces
4
11
Aileron Removal
Flight
Controls and Surfaces
4
11
Flight
Controls and Surfaces
4
11
Aileron
Aileron Control
Aileron
System Rigging
System
Aileron Trim Tab Actuator
Assembly
Flight
Controls and Surfaces
4
19
Aileron Trim Tab Actuator
Cleaning and Inspection
Flight
Controls and Surfaces
4
19
Aileron Trim Tab Actuator
Disassembly
Flight
Controls and Surfaces
4
19
Aileron Trim Tab Actuator Installation
Flight
Controls and Surfaces
4
19
Aileron Trim Tab Actuator Removal
Flight
Controls and Surfaces
4
16
Aileron Trim Tab Free
Flight
Controls and Surfaces
4
20
Flight
Controls and Surfaces
4
16
Power Plant
6
6
Power Plant
6
6
Aileron Trim Tab
Air Box,
Rigging
Engine
Air Box Installation,
ii
Play
Engine
Check
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
Air Box Removal,
or
Section Name
System Name
Power Plant
Engine
Section
Page
6
6
Air-Conditioning
Aft Blower Module Filter Clean
Heating
and
Cooling System
10
19
Air-Conditioning
Aft Blower Module Filter
Heating
and
Cooling System
10
19
Air-Conditioning
Aft Blower Module Installation
Heating
and
Cooling System
10
19
Air-Conditioning
Aft Blower Module Removal
Heating
and
Cooling System
10
19
Air-Conditioning
Clutch
Heating and Cooling System
10
16
Replacement
Air-Conditioning Compressor
Heating
and
Cooling System
10
17
Air-Conditioning Compressor
Belt Installation
Heating
and
Cooling System
10
17
Air-Conditioning Compressor
Belt Removal
Heating
and
Cooling System
10
16
Air-Conditioning Compressor
Belt Tension
Heating and Cooling System
10
17
Air-Conditioning Compressor
Installation
Heating
and
Cooling System
10
19
Air-Conditioning Compressor
Removal
Heating
and
Cooling System
10
18
Heating
and
Cooling System
10
18
1
17
Adjustment
Air-Conditioning Compressor Replacing
Air-Conditioning Compressor
Vendor Publications
General Information
Air-Conditioning
Condenser Blower Installation
Heating
and
Cooling System
10
17
Air-Conditioning
Condenser Blower Removal
Heating
and
Cooling System
10
17
Air-Conditioning
Condenser Installation
Heating
and
Cooling System
10
18
Air-Conditioning
Condenser Removal
Heating
and
Cooling System
10
18
Heating
and
Cooling System
10
16
Heating
and
Cooling System
10
20
Air-Conditioning Depressurizing
System
Air-Conditioning, Evacuating
the
Air-Conditioning, Evaporator
Blower Installation, Aft
Heating
and
Cooling System
10
22
Air-Conditioning, Evaporator
Blower Removal, Aft
Heating
and
Cooling System
10
22
Air-Conditioning, Evaporator
Blower Installation, Forward
Heating
and
Cooling System
10
22
Air-Conditioning, Evaporator
Blower Removal, Forward
Heating
and
Cooling System
10
20
Air-Conditioning, Evaporator
Mod Installation, Aft
Heating
and
Cooling System
10
22
Air-Conditioning, Evaporator
Mod Removal, Aft
Heating
and
Cooling System
10
22
Heating
and
Cooling System
10
20
Heating
and
Cooling System
10
20
Heating
and
Cooling System
10
20
Heating
and
Cooling System
10
19
Heating
and
Cooling System
10
16
Air-Conditioning, Evaporator Installation, Forward
Air-Conditioning Evaporator Removal,
Air-Conditioning Expansion
Air-Conditioning, Flushing
Air-Conditioning
E17
Valve
the
Adjustment
System
Functional Test
Forward
111
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
System
or
Name
Section
Section Name
Page
Air-Conditioning Leak Detection
Heating
and
Cooling System
10
16
Air-Conditioning Precautionary Servicing
Heating
and
Cooling System
10
13
Air-Conditioning Servicing
Ground
Handling and Servicing
2
6A
Air-Conditioning System
Heating
and
10
13
Air-Conditioning System Charging
Ground
Handling
Servicing
2
6A
Air-Conditioning System Lubrication
Ground
Handling and Servicing
2
6A
Air-Conditioning System Servicing
Ground
Handling
Servicing
2
6A
Air-Conditioning Troubleshooting
Heating
and Cooling
System
10
20
Heating
and
Cooling System
10
16
1
2, 7
Air-Conditioning
Unusual Noise
Cooling System
and
and
Aircraft Dimensions
General Information
Air Filter Installation
Utility Systems
11
31
Air Filter Removal
Utility Systems
11
31
Utility Systems
11
15
Utility Systems
11
15
Air Pressure
System Adjustment
Air Pressure
System
Inline Filter
Inspection
Electrical
System
13
12D
Electrical
System
13
12
Electrical
System
13
12
Alternator Control Bench Check
Electrical
System
13
12B
Alternator, Delcotron
Ground
2
8
Alternator and Generator Overhaul
Alternator Belt
Adjustment
Alternator Control
Adjustment
Handling and Servicing
Alternator Installation
(Belt Driven)
Electrical
System
13
10
Alternator Installation
(Gear Driven)
Electrical
System
13
10
Electrical
System
13
13
Alternator Lubrication
Alternator
Paralleling
Electrical
System
13
12
Alternator
Regulator Adjustment
Electrical
System
13
11
Alternator Removal
(Belt Driven)
Electrical
System
13
9
Alternator Removal
(Gear Driven)
Electrical
System
13
10
Alternator
System
Electrical
System
13
9
Alternator
Troubleshooting
Electrical
System
13
33
1
16
2
2A
11
41
Alternator, Vendor Publications
Anchoring
and
Anti-icing Fluid
iv
Mooring
Provisions
Indicator Calibration
General Information
Ground
Handling
Utility Systems
and
Servicing
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
Name
System
Anti-icing Maintenance, Propeller
Anti-icing Propeller
and Windshield
Boot Installation
Anti-icing Systems
Autopilot B-4, B-5,
B-7 Pressure
System
Autopilot B-4, B-5,
8-7 Pressure
System
Autopilot
H-14 Pressure
System
Autopilot
H-14 Pressure
System
Autopilot
Maintenance and
Deicer
and Deicer
Repair,
Section
Utility Systems
11
41
Utility Systems
11
42
Utility Systems
11
41
1
18
Utility Systems
11
15
Utility Systems
11
21
Utility Systems
11
19
Utility Systems
11
24
Utility Systems
11
78
General Information
Beech New-Matic Vendor Pubs
Autopilot,
Section Name
H-14
Page
Autopilot Rigging,
H-14
Utility Systems
11
78
Autopilot System,
H-14
Utility Systems
11
78
Utility Systems
17
84
General Information
1
17
Airframe
3
50
Airframe
3
50
Airframe
3
45
Autopilot Troubleshooting
Autopilot
Vendor Publications
Avionics
Compartment Door,
Baggage
Door
Adjustment,
Forward
Baggage
and
Forward
Baggage Door, Aft
Baggage Door,
Aft Removal and Installation
Airframe
3
45
Baggage Door,
Forward Removal and Installation
Airframe
3
50
Rigging, Utility
Airframe
3
44
Airframe
3
44
Airframe
3
44
Controls and Surfaces
4
61
Baggage
Door
Baggage Door, Utility
Baggage Door, Utility, Removal
and Installation
Balance Aileron
Flight
Balancing
Control Surfaces
Flight Controls
and Surfaces
4
61
Balancing
the Elevator
Flight Controls
and Surfaces
4
63
Balancing
the Rudder
Flight
Controls and Surfaces
4
69
Battery Capacity Reconditioning
Electrical
System
13
6
Battery Charging
Electrical
System
13
4
Battery Cleaning and inspecting
Electrical
System
13
8
E17
v
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Page
Section Name
Section
Electrical
System
13
1
Electrical
System
13
1
Battery, Nickel-Cadmium
Electrical
System
13
1
Battery Replacement, Collins Communications
Components Corporation Emergency Locator Transmitter
Electrical
System
13
74
Electrical
System
13
74
2
3
13
27
Item
Component
or
System
Name
Battery, Electrical System
Acid
Battery, Lead
Battery Replacement, Narco Emergency
Locator
Transmitter
and
Servicing
Battery Servicing
Ground
Battery Troubleshooting
Electrical
Battery Vendor Publications
General Information
1
15
Beechcraft Publications
General Information
1
17
Cooling System
10
16
Heating and Cooling System
10
16
Belt
Installation, Air-Conditioning Compressor
Belt Removal,
Air-Conditioning Compressor
Adjustment, Air-Conditioning Compressor
Belt Tension
Blower, Cabin Heater
Blower Installation,
Air-Conditioning
Blower Module, Aft
Evaporator
Blower Removal,
Brake
Air-Conditioning
Condenser
Condenser
Adjustment, Parking
Brake and Wheel
Assembly
Handling
Heating
System
and
Heating
and
Cooling System
10
16
Heating
and
Cooling System
10
5
Heating
and
Cooling System
10
16
Heating
and
Cooling System
10
19
Heating
and
Cooling System
10
16
Landing
Gear and Brake
System
5
1
Landing
Gear and Brake
System
5
3
1
8
2
4
Brake Fluid Reservoir
General Information
Brake Fluid
Ground
Servicing
Removal
(Cleveland)
Brake
Lining
Brake
Linkage Adjustment
Brake Master
Cylinder
Dynamic, Landing
Gear
Handling
Gear and Brake
System
5
5
Landing
Gear and Brake
System
5
1
Landing
Gear and Brake
System
5
6
Landing
Gear and Brake
System
5
81
Gear and Brake
System
5
1
and Brake
System
5
86
Gear and Brake
System
5
10
Relay
Brake
System Bleeding
Landing
Brake
System Troubleshooting
Landing Gear
Parking
Servicing
Landing
Brake
Brake Valve,
and
Landing
Brake Vendor Publications
General Information
1
17
Brake Wear Limits
General Information
1
8
vi
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
or
System
Name
Section
Section Name
Page
5
1
2
6B
General Information
1
9
General Information
1
7
Airframe
3
40
Cabin Door Removal and Installation
Airframe
3
38
Cabin Headliner, Removal and Installation
Airframe
3
37
Fuel
8
15
4
2
Power Plant
6
3
Airframe
3
48
Landing Gear
Brake Wear Limits
Break-in
Engine
Ground
Oil
Brush
Replacement Guide, Flap
Brush
Replacement, Propeller
Cabin Door
Motor
Deicer
Latching Adjustment
Cable, Fuel Selector
Cable Tension,
Valve Control
Flight
Cables, Engine Control
Cargo
Door
Handling
and
System
Servicing
System
Flight
Control
and Brake
Controls and Surfaces
Checking
Aileron Balance
Flight
Controls and Surfaces
4
62
Checking
Elevator Balance
Flight
Controls and Surfaces
4
65
Checking
Rudder Balance
Flight
Controls and Surfaces
4
69
11
Cleaning Airplane
Exterior
Ground
Handling
and
Servicing
2
Cleaning Airplane
Interior
Ground
Handling
and
Servicing
2
12A
Ground
Handling
and
Servicing
2
11
Cleaning Unpainted Surfaces
Ground
Handling
and
Servicing
2
11
Combustion Tube Pressure Test, Heater
Heating
and
Cooling System
10
8
Compressor, Air-Conditioning
Heating
and
Cooling System
10
17
Compressor Belt installation, Air-Conditioning
Heating
and
Cooling System
10
16
Heating
and
Cooling System
10
16
Heating and Cooling System
10
16
2
6A
Cleaning
Painted Surfaces
Compressor
Belt Removal,
Compressor Belt
Tension
Air-Conditioning
Adjustment, Air-Conditioning
Compressor Oil Level, Air-Conditioning
Condenser Blower Installation,
Condenser Blower Removal,
Condenser Installation,
Condenser Removal,
E17
Air-Conditioning
Air-Conditioning
Air-Conditioning
Air-Conditioning
and
Servicing
Ground
Handling
Heating
and
Cooling System
10
16
Heating
and
Cooling System
10
16
Heating
and
Cooling System
10
17
Heating
and
Cooling System
10
16
VII
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Section
Section Name
Name
Page
2
15
Controls and Surfaces
4
11, 15
Flight
Controls and Surfaces
4
2, 3
Control Column Arm Removal
Flight
Controls and Surfaces
4
2, 3
Control Column Chain Installation
Flight
Controls and Surfaces
4
7
Control Column Chain Removal
Flight
Controls and Surfaces
4
5
Control Column Chain
Flight
Controls and Surfaces
4
3, 9
and Surfaces
4
2, 5
Flight
Controls and Surfaces
4
9
Flight
Controls and Surfaces
4
10
2
2D
1
9
Consumable Materials Chart
Ground
Control Cables, Aileron
Flight
Control Column Arm Installation
Control Column,
Rigging
Flight Controls
Flight
Control Column Roller Adjustment
Control Column
Support Adjustment
Ground
Control Lock
Control Surface Travel,
Handling
Handling
and
and
Servicing
Servicing
General Information
Flight
Flight
Controls and Surfaces
4
1
Flight
Controls and Surfaces
4
11
Control Surfaces, Aileron Trim Tab
Flight
Controls and Surfaces
4
16
Control Surfaces
Balancing
Flight
Controls and Surfaces
4
61
Control Surfaces
Balancing,
Aileron
Flight
Controls and Surfaces
4
61
Control Surfaces
Balancing,
Elevator
Flight
Controls and Surfaces
4
63
Control Surfaces
Balancing,
Rudder
Flight
Controls and Surfaces
4
69
Flight
Controls and Surfaces
4
22
Control Surfaces, Elevator Trim Tab
Flight
Controls and Surfaces
4
33
Control Surfaces,
Flight
Controls and Surfaces
4
73
Control Surfaces, Rudder and Tab
Flight
Controls and Surfaces
4
49
Control Surfaces, Rudder Trim Tab
Flight
Controls and Surfaces
4
50
10
1,8
Power Plant
6
2
Power Plant
6
7, 8
Power Plant
6
4
Control Surfaces
Control Surfaces, Aileron
System
Control Surfaces, Elevator
Control
System,
System
Flaps
Heating
Heater
Controls-engine, Adjusting
Cowl
Flap
Actuator
Cowl
Flap Rigging
Rigging
Cylinder,
Brake Master
Cylinder,
Brake Master,
Cylinder
Differential
viii
Adjusting
the
Linkage
Compression Check
and
Cooling System
Landing
Gear and Brake
System
5
7
Landing
Gear and Brake
System
5
1
6
20
Power Plant
E17
RayZheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Section Name
Section
Cylinder, Oxygen
Utility Systems
11
1
Cylinder, Oxygen
General Information
1
8
Cylinder Retesting, Oxygen
Utility Systems
11
2
Defueling Airplane
Fuel
Deicer Boot
Cleaning
Ground
Deicer Boot
Coating
Component
Item
or
System
Name
Deicer Boot Installation
Page
8
24
2
12
Utility Systems
11
35
Utility Systems
11
28, 33, 60,
System
Handling and Servicing
63
Utility Systems
Deicer Boot Removal
11
28, 33, 60,
62
Deicer Boot
Repair
Utility Systems
11
26, 36
Deicer Boot
Resurfacing
Utility Systems
11
26
1
17
Utility Systems
11
68
Utility Systems
11
68
Utility Systems
11
55
Deicer Brush Block Resistance Check Goodrich
Utility Systems
11
59
Replacement, Goodrich
Utility Systems
11
55, 57
Utility Systems
11
53
General Information
Deicer Boot Vendor Publications
Deicer Brush Block Installation,
Deicer Brush Block Removal,
Deicer Brush Block
McCauley
McCauley
Replacement, Goodrich
Deicer Brush, Modular,
Goodrich
Deicer Brush
Replacement,
Deicer Brush
Replacement, Goodyear
Utility Systems
11
48
Deicer Brush
Replacement, McCauley
Utility Systems
11
66
Deicer Brush
Replacement, Propeller
General Information
1
7
Deicer Brush
Replacement, Propeller
Utility Systems
11
48, 53, 55,
57, 66, 68
Utility Systems
11
59
Utility Systems
11
56
Utility Systems
11
59
Electric
Resistance
Deicer
Brush-to-Slip Ring
Deicer
Continuity Test, Goodrich,
Electric
Deicer
Continuity Test, Goodrich,
Hot
Propeller
Prop
Deicer Electric
Propeller Goodrich
Utility Systems
11
52, 56
Deicer Electric
Propeller Goodyear
Utility Systems
11
48
E17
ix
RayZheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
Deicer Electric
or
System
Name
Propeller McCauley
Deicer Heat Test, Goodrich
Deicer Heat Test, Goodrich, Hot
Prop
McCauley
Deicer Heat Test,
Electric
Propeller
Deicer
Inspection,
Deicer
Machining Slip Ring, Propeller
Deicer Pressure
System
Deicer Pressure
System B-4, B-5,
Deicer Pressure
System
With H-14
Electric
B-7
Autopilot
Autopilot
Section Name
Section
Utility Systems
11
62
Utility Systems
11
56
Utility Systems
11
58
Utility Systems
11
66
Periodic
16
7
Utility Systems
11
60, 69
Utility Systems
11
21
Utility Systems
11
21
Utility Systems
11
24
Inspections
Page
Alcohol
Ground
Handling
and
Servicing
2
8
Deicer
Servicing, Lightweight Surface
Ground
Handling
and
Servicing
2
8
Deicer
Slip Ring Alignment, Goodrich
Utility Systems
11
59
Deicer
Slip Ring Alignment, McCauley
Utility Systems
11
68
Deicer
Slip Ring
Installation Goodrich
Utility Systems
11
59
Deicer
Slip Ring
Removal Goodrich
Utility Systems
11
59
Deicer
System, Lightweight
Surface
Utility Systems
11
4
Deicer
System,
Utility Systems
11
4, 26, 30
Utility Systems
11
55, 58, 65
Utility Systems
11
52
Utility Systems
11
26
Utility Systems
11
14
10
15
Deicer, Propeller
Deicer Timer
Surface
Check, Electric Propeller
Deicer Timer Check, Electric
Deicer Timer
Deicer
Propeller, Goodyear
Relay Adjustment
Troubleshooting,
Reservoir
Type
Depressurizing Air-Conditioning
Diagram, Stations (TC-1
Heating
and
Cooling System
and
After)
Airframe
3
1
Diagram,
Stations
(TE-1
and
After)
Airframe
3
2
Diagram,
Stations
(TH-1
and
After)
Airframe
3
3
Power Plant
6
18
General Information
1
7
Airframe
3
49
Airframe
3
45
Airframe
3
49
Airframe
3
49
Differential
Compression
Check
Dimensions of Aircraft
Door
Adjustment, Cargo
Door Aft,
Baggage
Door, Aft Half Cargo,
Door, Cargo
x
Adjustment
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Name
Section
Section Name
Page
Door, Forward Baggage and Avionics Compartment
Airframe
3
50
Door, Forward Baggage Removal and Installation
Airframe
3
50
Door, Forward Half Cargo,
Airframe
3
49
Airframe
3
47
Airframe
3
49
Airframe
3
49
Airframe
3
49
Airframe
3
38
Airframe
3
50
Airframe
3
49
Door, Utility
Airframe
3
44
Door, Utility Baggage
Airframe
3
44
Window, Cabin
Airframe
3
54
Adjustment,
Airframe
3
40
Doors, Cabin
Airframe
3
38
Dual Control Arm Installation
Flight
Controls and Surfaces
4
5
Dual Control Arm Removal
Flight
Controls and Surfaces
4
3
Dual Control Arm
Flight
Controls and Surfaces
4
5
Dual Control Columns
Flight
Controls and Surfaces
4
5
Dual Pressure
Regulator Valve Installation
Utility Systems
11
31
Dual Pressure
Regulator
Utility Systems
11
30
5
81
Utility Systems
11
56, 59
Utility Systems
11
56, 58, 66
Utility Systems
11
59
Utility Systems
11
52, 55, 58,
Door Handle Removal and
Door
Adjustment
Installation, Interior
Installation, Cargo
Door Latch Pin
Adjustment
Door Lubrication,
Cargo
Door Removal and Instailation, Cabin
Door Removal and Installation, Forward
Door Removal,
Door
Doors
Dynamic
Baggage
Cargo
Brake
Cabin
Rigging
Valve Removal
Relay, Landing Gear
Landing
Electric Deicer
System
Check
Electric Deicer
System
Check Heat,
Electric Deicer
System
Check Resistance,
Electric Deicer
System
Check Timer
Continuity, Propeller
Propeller
Propeller
Gear and Brake
System
65
Electric Trim Tab Actuator Installation
E17
Flight
Controls and Surfaces
4
47
xi
Raythe6n Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Section
Section Name
Name
Page
Surfaces
4
46
Flight
Controls and Surfaces
4
47
Electric Trim Tab Cable Removal
Flight
Controls and Surfaces
4
47
Electric Trim Tab
Flight
Controls and Surfaces
4
46
Electric Trim Tab Actuator Removal
Flight Controls and
Electric Trim Tab Cable Installation
System
Electrical, Alternator Control Adjustment
Electrical
System
13
12
Electrical, Alternator Control Check
Electrical
System
13
12B
Electrical Deicer Boots,
Utility Systems
11
60, 62
Utility Systems
11
48, 52, 62
Electrical Deicer Slip Ring, Propeller
Utility Systems
11
59, 68
Electrical
System
Electrical
System
13
1
Electrical
System Alternator, Voltage Regulator Adjustment
Electrical
System
13
11
Electrical
System, Battery
Electrical
System
13
1
Electrical
System, Battery Servicing
Ground
2
3
Electrical
System
15
4
13
12C
5
86
13
16
Electrical Deicer,
Propeller
Propeller
Overhaul and
Replacement Schedule
Handling
Overhaul and
and
Servicing
Replacement
Schedule
Electrical
Check
Electrical
System Overvoltage
Electrical
System Troubleshooting, Landing
Landing
Gear
System
Gear and Brake
System
Electrical Utilization Load Chart
Electrical
Elevator
Flight
Controls and Surfaces
4
63
Flight
Controls and Surfaces
4
27
and Surfaces
4
23
Balancing
Elevator Down
Spring
Loads
System
Elevator Installation
Flight Controls
Elevator Removal
Flight
Controls and Surfaces
4
22
Flight
Controls and Surfaces
4
26, 28
Flight
Controls and Surfaces
4
23
and Surfaces
4
22
1
14
Elevator
Rigging
Elevator Skin
Replacement
After;
(TC-547
and
Elevator
System
Elevator Travel
TE-1 and
After;
TH-1 and
After)
Flight Controls
General Information
Gage
Elevator Trim Tab Actuator
Elevator Trim Tab Actuator
(TC-1
thru TC-1143; TE-I
Elevator Trim Tab Actuator
(TC-1144
xii
Assembly
thru TE-617)
Assembly
and After; TE-618 and After; TH-1 and
Flight
Controls and Surfaces
4
35
Flight
Controls and Surfaces
4
39
Flight
Controls and Surfaces
4
40
After)
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
item
or
System
Elevator Trim Tab Actuator
(TC-1
Cleaning and
TE-617)
Lubrication
Flight
Page
Controls and Surfaces
4
38
and Surfaces
4
40
thru TC-1143; TE-1 thru
Elevator Trim Tab Actuator
(TC-1144
Cleaning
and After; TE-618 and
Elevator Trim Tab Actuator
thru
TC-1143;
and
After;
TH-1 and
Flight Controls
After)
Flight
Controls and Surfaces
4
38
Disassembly
TE-617)
Flight
Controls and Surfaces
4
38
Disassembly
Flight
Controls and Surfaces
4
39
Flight Controls and Surfaces
4
46
TE-1 thru
Elevator Trim Tab Actuator
(TC-1144
and Lubrication
Coding
Elevator Trim Tab Actuator Color
(TC-1
Section
Section Name
Name
After; TE-618 and After; TH-1 and After)
Elevator Trim Tab
Actuator, Electric
Elevator Trim Tab Actuator Installation
Flight
Controls and Surfaces
4
47
Elevator Trim Tab Actuator,
Flight
Controls and Surfaces
4
12
Elevator Trim Tab Actuator Removal
Flight
Controls and Surfaces
4
35
Elevator Trim Tab Free
Flight Controls and Surfaces
4
41
Flight
Controls and Surfaces
4
43
Flight
Controls and Surfaces
4
34
Flight
Controls and Surfaces
4
47
Flight
Controls and Surfaces
4
33
Flight
Controls and Surfaces
4
46
Elevator Trim Tab Horn
Magnetic
Play
Clutch
Check
Repair
Elevator Trim Tab Indicator Cable
Elevator Trim Tab
Magnetic
Elevator Trim Tab
Rigging
Elevator Trim Tab
System,
Replacing
Clutch
Electric
Electrical
System
13
40
Battery Replacement,
Components Corporation
Electrical
System
13
74
Emergency Locator Transmitter Battery Replacement,
Electrical
System
13
74
Electrical
System
13
41
1
17
12
1
Emergency Location Transmitter
Emergency
Locator Transmitter
Collins Communications
Narco
Emergency
Locator Transmitter
Emergency
Locator Transmitter, Vendor Publications
Testing
General Information
Enamel Paints
Aircraft Finishes
Engine
General Information
1
6
Power Plant
6
2
13
9
Engine
Air Box
Engine Alternators
Electrical
Engine Alternators, Servicing
Ground
Handling
Servicing
2
8
Engine Cleaning
Ground
Handling and Servicing
2
12
Engine Control Cables
Power Plant
6
3
E17
System
and
xiii
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
Engine Controls, Adjusting
Engine
Flap
Cowl
Actuator
Rigging
Engine Cylinder Differential Compression
Section
Section Name
System Name
Check
Page
Power Plant
6
6
Power Plant
6
3
Power Plant
6
23
Engine Cylinder
Head
Temperature
Bulb
Power Plant
6
2
Engine Cylinder
Head
Temperature
Bulb Installation
Power Plant
6
3
Engine Cylinder
Head
Temperature
Bulb Removal
Power Plant
6
3
General Information
1
6
Power Plant
6
2
6
4
13
13
Power Plant
6
4
Power Plant
6
5
Power Plant
6
5
2
6B
Engine Firing
Order
Engine
Fuel
Injector Line Nuts
Engine
Fuel Injector Pump
Power Plant
Engine
Generators
Electrical
Engine Ground Running
and
Warm-up
System
Engine
Idle Mixture
Engine
Idle
Engine
Induction Manifold Drain
Ground
Engine
Installation
Power Plant
6
1
Power Plant
6
8
Engine Magnetos
Power Plant
6
5
Engine Magnetos Timing
Power Plant
6
6
2
6B
Speed Adjustment
Engine Magneto
Engine Oil,
Adjustment
Breaker Point
Adjustment
Ground
Break-in
Handling
Handling
and
and
Servicing
Servicing
Engine
Oil
Capacity
General Information
1
6
Engine
Oil Pressure
General Information
1
6
Engine
Oil Pressure
Power Plant
6
5
Power Plant
6
5
6
1
2
6A
6
5
2
25
6
1
2
13
13
15
6
3
Engine Oil
Adjustment
Pressure Fluctuation
Adjustment
Engine
Oil Radiator
Power Plant
Engine
Oil
System
Ground
Engine
Oil
Temperature
Power Plant
Ground
Engine Oils, Approved
Engine
Engine
Starter
Engine
Throttle
xiv
Handling
and
and
Servicing
Servicing
Power Plant
Removal
Engine Spark Plug
Handling
Ground
Chart
Handling
Electrical
Warning
Horn Cam
System
Power Plant
and
Servicing
E17
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Engine Troubleshooting
Engine
Section
Section Name
Name
Vendor Publications
Page
Power Plant
6
19
General Information
1
15
Epoxy Paint Colors
Aircraft Finishes
12
4
Epoxy Paints
Aircraft Finishes
12
2
Aircraft Finishes
12
3
Paint
Epoxy Primer,
Air-Conditioning System
Heating
and
Cooling System
10
17
Cleaning
Heating
and
Cooling System
10
19
Replacement
Heating
and
Cooling System
10
19
Heating
and
Cooling System
10
19
Heating
and
Cooling System
2
6A
External Power
Ground
Handling
2
2E
Fiberglass Repair
Airframe
3
56
Filter, Central Instrument Air
Ground
Handling
2
9
Heating
and
10
19
11
4
2
9
11
4
Evacuating
the
Evaporator
Blower Filter
Evaporator
Blower Filter
Evaporator
Blower Module
Expansion
Filter
Valve
Adjustment, Air-Conditioning
Cleaning, Evaporator
Blower
and
and
Servicing
Servicing
Cooling System
Filter, Gyro Air
Utility Systems
Filter, Gyro Instrument Air
Ground
Filter, Gyro Instrument Air
Utility Systems
Filter, Heater Fuel Servicing
Ground
Handling
and
Servicing
2
6
Filter, Induction Air Cleaning
Ground
Handling
and
Servicing
2
12
11
6, 15
2
6B
10
19
12
1
Filter
Inspection,
Pressure
System
Replacement, Evaporator
and
Servicing
Utility Systems
Filter, Oil Replacement
Filter
Handling
Blower
Ground
Handling
Heating
and
and
Servicing
Cooling System
Finishes, Aircraft
Aircraft Finishes
Flap Actuator Assembly
Flight
Controls and Surfaces
4
84
Flight
Controls and Surfaces
4
83
Flight
Controls and Surfaces
4
84
15
3
Disassembly
Flap
Actuator
Flap
Actuator Lubrication
Flap
and
Flight
Control Overhaul and
Replacement
Overhaul and
Replacement
Schedule
E17
xv
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
System
Component
Item
Flap Control
and Indicator
Flap
or
Troubleshooting
Drive Cable Connection
Flap Gearbox
Section
Section Name
Name
and Motor
Electrical
System
Page
13
35
Flight
Controls and Surfaces
4
77
Flight
Controls and Surfaces
4
77, 78, 79
Flap
Inner Flex Shaft Installation
Flight
Controls and Surfaces
4
82
Flap
Inner Flex Shaft Removal
Flight
Controls and Surfaces
4
81
Flight
Controls and Surfaces
4
73
Flight
Controls and Surfaces
4
74
Flight
Controls and Surfaces
4
77, 78, 79
Flight
Controls and Surfaces
4
79
Flight
Controls and Surfaces
4
79
Flight
Controls and Surfaces
4
78
Flight
Controls and Surfaces
4
78
and Gearbox Overhaul
Flight
Controls and Surfaces
4
79
Flap
Motor and Gearbox Removal
Flight
Controls and Surfaces
4
77
Flap
Motor Brush
1
9
Flap
Position Indicator
Flap
Removal
Flap Installation
Adjustment
Flap
Limit Switch
Flap
Motor and Gearbox
Flap
Motor and Gearbox
Assembly
Flap
Motor and Gearbox
Cleaning
and
Inspection
Flap Motor and Gearbox Disassembly
Flap
Motor and Gearbox Installation
Flap Motor
General Information
Replacement Guide
Adjustment
Flight
Controls and Surfaces
4
76
Flight
Controls and Surfaces
4
73
Flap Shaft
Installation
Flight
Controls and Surfaces
4
81
Flap Shaft
Removal
Flight
Controls and Surfaces
4
79
Flight
Controls and Surfaces
4
73
Flight
Controls and Surfaces
4
73
Flight
Controls and Surfaces
4
83
Flight
Controls and Surfaces
4
79
Flaps, Three-Position
Flight
Controls and Surfaces
4
75
Flaps, Two-Position
Flight
Controls and Surfaces
4
75
1
11
2
10
8
19
15
3
Flap Tracks
Wear Limits
Flaps
Flaps,
Actuator
Flaps,
Motor and Gearbox
Flare
Assembly
General Information
Fitting Torque Chart
Flared
Fitting Installation
Ground
Flared
Fittings, Fuel, Installation
Fuel
Flight Control and Flap Overhaul
and
Replacement
Handling
and
Servicing
System
Overhaul and
Replacement
Schedule
Flight
xvi
Control Column
Flight
Controls and Surfaces
4
2,
5
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Page
Flight Controls
and Surfaces
4
11
Balancing
Flight Controls
and Surfaces
4
61
Rigging
Flight
Controls and Surfaces
4
11,15
Flight
Controls and Surfaces
4
16
Flight
Controls and Surfaces
4
1
Flight Controls and Surfaces
4
2
Flight Controls and Surfaces
4
22
and Surfaces
4
63
Flight Controls,
Aileron
Flight Controls,
Aileron
Flight Controls,
Aileron
Flight Controls,
Aileron Trim Tab
Flight
Section
Section Name
Name
Controls and Surfaces
Flight Controls, Effect of Temperature
Flight Controls,
Elevator
Flight Controls,
Elevator
Balancing
Flight Controls
Flight Controls,
Elevator
Rigging
Flight
Controls and Surfaces
4
26, 28
Flight Controls,
Elevator Trim Tab
Flight
Controls and Surfaces
4
33
Flight Controls, Rudder
Flight
Controls and Surfaces
4
49
Flight Controls, Rudder Balancing
Flight Controls and Surfaces
4
69
Flight
Controls and Surfaces
4
49
Flight
Controls and Surfaces
4
50
1
9
Cooling System
10
17
Controls and Surfaces
4
9
Rigging
Flight Controls,
Rudder
Flight Controls,
Rudder Trim Tab
Flight
General Information
Control Surface Travel
Flushing
the
Heating
System, Air-Conditioning
and
Forward Outer Tube Rollers
Flight
Fresh Air Vent Blower Installation
Heating
and
Cooling System
10
23
Fresh Air Vent Blower Removal
Heating
and
Cooling System
10
23
Heating and Cooling System
10
23
Fresh Air Vent Blower
System
Fuel Boost
Pump Installation
Fuel
System
8
20
Fuel Boost
Pump Removal
Fuel
System
8
19
Fuel
System
8
18A
Fuel
System
8
12
Fuel
System
8
14
Fuel
System
8
12
Fuel
System
8
12
Fuel
System
8
14
Fuel
System
8
12
Fuel
System
8
13
Fuel
System
8
12
Fuel Cell
Flapper
Valve
Fuel Cell Installation,
Inspection
Auxiliary
Fuel Cell Installation, Box Section
Fuel Cell Installation, Inboard Lead
Edge
Fuel Cell Installation, Main
Fuel Cell Installation, Outboard Lead
Fuel Cell Removal,
Edge
Auxiliary
Fuel Cell Removal, Box Section
Fuel Cell Removal, Inboard
E17
Leading Edge
xvii
Raythean Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
or
System
Name
Fuel Cell Removal, Main
Fuel Cell Removal, Outboard
Leading Edge
and Care
Section
Section Name
Page
Fuel
System
8
11
Fuel
System
8
14
Fuel
System
8
20
Fuel Cell
Repair
Fuel Cell
Repair, Goodyear
Fuel
System
8
20
Fuel Cell
Repair, Uniroyal
Fuel
System
8
20
Fuel
System
8
19
Fuel
System
8
18
10
5
2
6
Fuel Cell Vent Line, External
Fuel Cells, Installation of Velcro
Fuel
Tape
Discharge Nozzle, Heater
Fuel Filter, Heater
Fuel Flared
Fuel Flow
Installation
Fittings,
Maintenance Practices
Indicating
Fuel Flow Indicator
Fuel Flow
System
Calibration
Fuel, Full Throttle Pressure Adjustment
Cooling System
Heating
and
Ground
Handling
and
Servicing
Fuel
System
8
19
Fuel
System
8
18
Fuel
System
8
18
Power Plant
6
12
Power Plant
6
7
Fuel
Injector Pump
Installation
Power Plant
6
8
Fuel
Injector Pump
Removal
Power Plant
6
8
Fuel
8
16
6
5, 7, 9
2
6
Fuel Level Transmitters
Fuel Pressure
System
Power Plant
Adjustment
Heater, Servicing
Ground
Handling
and
Servicing
Fuel
Pump
Fuel
Quantity Gages, Adjusting
Fuel
System
8
18
Fuel
Quantity Gages, Empty Reading Adjustment
Fuel
System
8
18
Fuel
Quantity Gages,
Fuel
System
8
18
Fuel
Quantity Indicator, Adjusting
Fuel
System
8
16
Fuel
Quantity
13
36
Full
Indicator
Reading Adjustment
Troubleshooting
Fuel Selector Valve Control Cable
Fuel Selector
Valve, Installation
Fuel Selector Valve,
Removing
Fuel Strainer Screens, Main
Electrical
System
Fuel
System
8
15
Fuel
System
8
15
Fuel
System
8
14
2
6
8
1
Ground
Handling
and
Servicing
Fuel
System
Fuel
Fuel
System Adjustment
Power Plant
6
9
Fuel
System Capacities
Fuel
8
4
XVIII
System
System
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Section
Section Name
Name
Page
Fuel
System Capacity
General Information
1
7
Fuel
System Grades
General Information
1
7
Fuel
System
Overhaul and
15
3
Fuel
System
Pressure
1
7
Fuel
System Servicing
2
6
Fuel
System
1
15
13
30
Power Plant
6
12
Fuel Trans
Replacement Schedule
Overhaul and Replacement
Schedule
General Information
Adjustment
Ground
Handling
and
Servicing
General Information
Vendor Publications
Electrical
Regulator Troubleshooting
Full Throttle Fuel Pressure
System
Fuselage
Access
Openings (Model 55’s)
Airframe
3
4
Fuselage
Access
Openings (Model 58)
Airframe
3
5
Fuselage, Wing Forward Spar Carry-Through Structure
Inspection Without Repair Kit
Airframe
3
27
Structure
Airframe
3
27
Structure
Airframe
3
29
Fuel
System
8
18
Fuel
System
8
18
Fuel
System
8
18
2
10
4
77, 78, 79
Fon/vard
Fuselage, Wing
Inspection
With
Repair
Spar Carry-Through
Kit
Fuselage, Wing Forward Spar Carry-Through
Repair/inspection
Gage Adjusting,
Fuel
Quantity
Empty Reading
Gages,
Fuel
Quantity, Adjustment
for
Gages,
Fuel
Quantity, Adjustment
for Full
Reading
Gaskets and Seals Lubrication
Ground
Gearbox, Flap
Flight
Handling and Servicing
Controls and Surfaces
Electrical
System
13
12
Generator Brush Wear Limits
Electrical
System
13
13
Generator Overhaul
Electrical
System
13
11
Generator Belt
Adjustment
Generator
Paralleling Relay
Electrical
System
13
15
Generator
Regulator Adjustment
Electrical
System
13
13
Generator
System
Electrical
System
13
13
Generator
Troubleshooting
Electrical
System
13
29
E17
xix
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Generator Vendor Publications
Glare Shield Installation
TH-1389, TH-1396 and
(All TC, TE,
After)
Glare Shield Installation
(TH-1389,
Glare Shield Removal
(All TC, TE,
After)
Section
Section Name
Name
and TH Serials
TH-1396 and
Except
After)
and TH Serials
Except
Page
General Information
1
16
Airframe
3
36
Airframe
3
36
Airframe
3
36
Airframe
3
36
General Information
1
6B
Propeller
7
3
2
1
6
9
11
4
2
9
TH-1389, TH-1396 and
Glare Shield Removal
Governor
(TH-1389,
TH-1396 and
Listing, Propeller
Governor, Propeller
Ground
Handling
Ground
Handling
After)
Ground
and
Warm-Up
System
Gyro
Air Filter-vacuum
Gym
Instrument Air Filter
Handling
and
Servicing
Power Plant
Utility Systems
Ground
Handling
and
Servicing
Headliner Installation
Airframe
3
37
Headliner Removal
Airframe
3
37
Heater Blower
Heating
10
5
Heater Blower Vendor Publications
General Information
1
16
and
Cooling System
Heating
and
Cooling System
10
4, 10
Heating
and
Cooling System
10
10
Heater Combustion Tube Pressure Test
Heating and Cooling System
10
8
Heater Control
Heating
and
Cooling System
10
1,8
Heating
and
Cooling System
10
5
Ground
Handling
and
Servicing
2
6
Ground
Handling
and
Servicing
2
5
Points
Heating
and
Cooling System
10
1
Unit
Heating
and
Cooling System
10
5, 8
Heater Installation
Heating
and
Cooling System
10
11
Heater Overhaul
Heating
and
Cooling System
10
4, 8
Heater
Cleaning
Heater Combustion Chamber
Heater Fuel
System
Discharge
Nozzie
Heater Fuel Filter
Heater Fuel
Pump Servicing
Heater
Igniter
Heater
Ignition
xx
Inspection
E17
Raythean Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Item
Component
or
System Name
Section
Section Name
Page
Heating
and
Cooling System
10
1,8
Heating
and
Cooling System
10
4, 10
Heater Removal
Heating
and
Cooling System
10
10
Heater Removal and Installation
Heating
and
Cooling System
10
4
Heater Solenoid Valve
Heating
and
Cooling System
10
4
Heater, Overheat Thermostat
Heater Radiator
Inspection
Heater
Spark Plug
Heating
and
Cooling System
10
5, 11
Heater
Spark Plug Gap
Heating
and
Cooling System
10
1,8
Heater
Troubleshooting
Heating and Cooling System
10
6, 12
1
16
2
2E
Heater Vendor Publications
General Information
Hoisting Airplane
Ground
Horizontal Stabilizer
Flight
Controls and Surfaces
4
61
Horizontal Stabilizer Installation
Flight
Controls and Surfaces
4
61
Horizontal Stabilizer Removal
Flight Controls
and Surfaces
4
61
Horn, Elevator Trim Tab
Flight
Controls and Surfaces
4
43
5
82
6
9, 11
13
33
10
5, 8
8
16
4
76
2
12
Horn Switch
Idle
Speed
Adjustment,
and Mixture
Throttle
Warning
Adjustment
Ignition System Troubleshooting
Ignition Unit,
Landing
Adjusting, Fuel Quantity
Fuel
Indicator
Adjustment, Flap Position
Flight
System
Controls and Surfaces
Ground
Handling
and
Servicing
Deicer 100-Hour
Periodic
Inspections
16
16
Deicer 50-Hour
Periodic
Inspections
16
16
Periodic
Inspections
16
1
Electric Deicer
Periodic
Inspections
16
16
Spar Carry-Through
Airframe
3
29
Airframe
3
8
Propeller
Inspection,
Electric
Propeller
Inspection,
Periodic
Inspection,
Periodic
E17
Cooling System
2
Electric
Propeller
Wing Tip
and
16
Inspection,
Installation of
System
Inspections
1 GO-Hour
Forward
System
Periodic
Inspection,
Inspection, Wing
Servicing
Gear and Brake
Electrical
Indicator
Cleaning
and
Power Plant
Heating
Cabin Heater
Induction Air Filter
Handling
xxi
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Section
Section Name
Name
Instrument Access
Ground
Instrument Air Filter
Utility Systems
Handling
and
Servicing
Page
2
9
11
4, 10, 13,
15
Instrument Air Filter, Central
Ground
Handling
and
Servicing
2
9
Instrument Air Filter
Ground
Handling
and
Servicing
2
9
Ground
Handling
and
Servicing
2
9
15
3
11
13
Instrument Air
Gyro
Servicing
Overhaul and
Replacement Schedule
Instrument Overhaul and
Replacement
Schedule
Instrument Pressure
Instrument
Interior
Utility Systems
System
Wedge Lights
Cleaning
Ground
Handling
and
Servicing
2
8
Ground
Handling
and
Servicing
2
12A
Interior Door Handle Removal and Installation
Airframe
3
47
Jacking Airplane
Ground Handling and Servicing
2
1
Landing
Gear Actuator
Overhaul
Landing
Gear and Brake
System
5
78
Landing
Gear Actuator, Removal and Installation
Landing
Gear and Brake
System
5
78
2
12
Landing Gear
and
Landing Gear Disassembly,
Landing
Gear
Ground
Tires, Cleaning
Dynamic
Nose
Brake
Relay, Removal
and
Handling
and
Servicing
Landing
Gear and Brake
System
5
48
Landing
Gear and Brake
System
5
81
Landing
Gear and Brake
System
5
86
Landing
Gear and Brake
System
5
28
Installation
System Troubleshooting
Landing
Gear Electrical
Landing
Gear
Landing
Gear
Main, Assembly
Landing
Gear and Brake
System
5
30
Landing
Gear
Main, Disassembly
Landing
Gear and Brake
System
5
26
1
9
Landing Gear,
Inspection
and Parts
Main Extension
Replacement,
Main
General Information
Landing
Gear
Main, Installation
Landing
Gear and Brake
System
5
24
Landing
Gear
Main, Lubrication
Landing
Gear and Brake
System
5
24
xxii
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
or
Section
Section Name
Name
System
Page
Landing Gear
Main, Overhaul
Landing
Gear and Brake
System
5
25, 34
Landing Gear
Main, Removal
Landing
Gear and Brake
System
5
24
Landing Gear
Main, Wear Tolerances
Landing
Gear and Brake
System
5
31
Brake
System
5
13
Landing
Gear and Brake
System
5
13
Landing
Gear and Brake
System
5
81
Landing Gear and Brake System
5
53
Gear and Brake
5
48
1
9
Landing
Gear Maintenance and
Landing
Gear Microswitch
Landing Gear and
Adjustment
Adjustment
Landing Gear Motor
Landing
Gear Nose
Assembly
Landing
Landing Gear Nose Disassembly
Landing
System
General Information
Gear Nose Extension
Landing
Gear and Brake
System
5
51
Nose Lubrication
Landing
Gear and Brake
System
5
46
Landing Gear
and Brake
System
5
46
Landing Gear
Nose
Landing Gear
Inspection
and Parts
Replacement
Landing
Gear
Nose Removal and Installation
Landing
Gear
Nose
Servicing
Landing
Gear and Brake
System
5
46
Landing Gear
Nose
Shimmy Damper Assembly
Landing
Gear and Brake
System
5
72
Landing Gear
Nose
Shimmy Damper Servicing
Ground
Handling
2
4
Landing Gear
Nose
Shimmy Damper
Landing
Gear and Brake
5
73
15
1
13
35
Wear Tolerances
Landing Gear Overhaul and Replacement Schedule
Overhaul and
and
Servicing
System
Replacement
Schedule
Landing Gear
Position Indicator
Landing Gear
Position
Troubleshooting
Light Adjustment
Landing Gear Pressure Switch Adjustment
Landing
Gear
Rigging
Landing Gear Safety Switch
Landing
Gear
Check
Safety System
Pressure Switch
Adjustment
Landing Gear Servicing
Landing Gear Servicing
Shock Struts
Landing Gear Servicing
Uplock
Roller
Bearing
System
Electrical
Landing
Gear and Brake
System
5
81
Landing
Gear and Brake
System
5
13
Landing
Gear and Brake
System
5
18
Landing
Gear and Brake
System
5
13
Landing
Gear and Brake
System
5
13
Ground
Handling
and
Servicing
2
4
Ground
Handling
and
Servicing
2
4
Ground
Handling
and
Servicing
2
5
Landing
Gear and Brake
System
5
55, 64
Landing Gear System
Landing
Gear and Brake
System
5
11
Landing Light Troubleshooting
Electrical
13
36
3
49
Landing Gear
Latch Pin
E17
Shock Strut Wear Tolerances, Nose
Adjustment,
Door
Airframe
System
xxiii
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Section
Section Name
Name
Page
Leading Edge, Wing Panel,
Installation
Airframe
3
10
Leading Edge, Wing Panel,
Removal
Airframe
3
10
Fuel
8
22
10
15
8
22
Leakage
Checks and
Leak Detection,
Leak Test Wet
Leather
Repairs (Wet Wing Tip)
Heating
Air-Conditioning
Fuel
Wing Tip
Upholstery, Cleaning
Leveling Airplane
Light
Bulb
Guide
Replacement
System
and
Cooling System
System
Ground
Handling
and
Servicing
2
12A
Ground
Handling
and
Servicing
2
2E
Electrical System
13
24
Light-Strobe,
Bullock Unit
System
Electrical
System
13
37
Light-Strobe,
Grimes Unit
System
Electrical
System
13
38
Light Troubleshooting, Landing
Electrical
System
13
36
Light Troubleshooting, Navigation
Electrical
System
13
36
Lights, Wedge
Ground
Handling
and
Servicing
2
9
Lock, Control
Ground
Handling
and
Servicing
2
2D
Lubricants, Table of Thread
Ground
Handling
and
Servicing
2
14
Lubrication, Alternators
Electrical
13
13
Lubrication Chart
Ground
Handling
and
Servicing
2
21
Lubrication, Gaskets and Seals
Ground
Handling
and
Servicing
2
11
Lubrication, Starter
Electrical
13
15
Lubrication, Thread
Ground
Handling and Servicing
2
11
Lubrication, Up Lock Rollers
Ground
Handling
Servicing
2
5
System
System
and
Magnetic
Clutch Installation
Flight
Controls and Surfaces
4
47
Magnetic
Clutch Removal
Flight
Controls and Surfaces
4
47
Magnetic
Clutch
Flight
Controls and Surfaces
4
47
Power Plant
6
18, 19
Power Plant
6
15
Magneto Breaker Point Adjustment, Slick
Power Plant
6
20
Magneto Installation
Power Plant
6
16, 20, 21
Torque Test
Magneto, Bendix Timing
Magneto
xxiv
Breaker Point
Adjustment,
Bendix
E17
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Section
Section Name
Name
Page
Power Plant
6
20
Power Plant
6
20
Magneto Removal
Power Plant
6
20
Magneto Timing
General Information
1
6
General Information
1
16
Magnetos
Power Plant
6
13
Magnetos Drop-Off Check
Power Plant
6
14
2
8
6
14
Magneto Point Gap and Timing
Magneto Preparation
Magneto
for Installation
Vendor Publications
’Ground Handling and Servicing
Magnetos Servicing
Power Plant
Magnetos Timing
Brake
System
5
30, 39
Gear and Brake
System
5
28, 37
Landing Gear and Brake System
5
26, 34
Landing
Gear and Brake
System
5
24
Landing
Gear
Assembly
Landing Gear and
Landing
Repairs
Gear
Cleaning, Replacement Parts and
Landing
Main
Main
Main Landing Gear Disassembly
Gear Installation
Main
Landing
Main
Landing Gear-Overhaul
Landing
Gear and Brake
System
5
25, 34
Main
Landing
Gear Removal
Landing
Gear and Brake
System
5
24
Main
Landing
Gear Strut Extension
General Information
1
9
Main
Landing
Gear Wear Tolerances and
5
31, 41
2
6A
Inspection
Landing Gear and
Brake
System
Procedures
Manifold Drain,
Engine
Induction
Master
Cylinder Linkage Adjustment
Master
Cylinder
Master
Cylinder Removing
Measuring
and
Installing
Rudder and Rudder Trim Tab Travel
Rigging
Microswitch Adjustment, Landing Gear
Mooring
and
Motor Brush
Handling
Landing
Landing
Servicing
Gear and Brake
System
5
1
Brake
System
5
7
Gear and Brake
System
5
6
4
55
6
8
5
13
Flight Controls
and Surfaces
Power Plant
Landing
Gear and Brake
System
Anchoring Provisions
Ground Handling and Servicing
2
2A
Replacement Guide, Flap
General Information
1
9
4
77, 78, 79
5
81
Controls and Surfaces
Motor, Flap
Flight
Motor, Landing Gear
Landing
E17
and
Landing Gear and
Overhaul
Mechanical Cowi Flap
Ground
Gear and Brake
System
xxv
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
Nacelle and Wheel Well
Section
Section Name
System Name
Ground
Cleaning
Handling
Electrical
Navigation Light Troubleshooting
and
Servicing
System
Page
2
12
13
36
Landing
Gear and Brake
System
5
53, 62
Landing
Gear and Brake
System
5
51, 59
Landing
Gear and Brake
System
5
48, 58
Gear Installation
Landing
Gear and Brake
System
5
47
Gear Lubrication
Landing
Gear and Brake
System
5
46
Landing Gear-Overhaul
Landing
Gear and Brake
System
5
48, 58
Landing
Gear Removal
Landing
Gear and Brake
System
5
47
Nose
Landing
Gear Retract Mechanism
Landing
Gear and Brake
System
5
74
Nose
Landing
Gear
Landing
Gear and Brake
System
5
46
Nose
Landing Gear Shimmy Damper Assembly
Landing
Gear and Brake
System
5
72
Nose
Landing
Gear
Shimmy Damper Disassembly
Landing
Gear and Brake
System
5
68
Nose
Landing
Gear
Shimmy Damper
Landing
Gear and Brake
System
5
67
Nose
Landing
Gear
Shimmy Damper-Overhaul
Landing
Gear and Brake
System
5
67
Nose
Landing Gear Shimmy Damper Removal
Landing
Gear and Brake
System
5
67
Nose
Landing
Shimmy Damper Servicing
Landing
Gear and Brake
System
5
67
Landing
Gear and Brake
System
5
73
1
9
Nose
Landing
Gear
Assembly
Nose
Landing
Gear
Cleaning, Replacement
Repai
rs
Nose
Landing
Gear
Disassembly
Nose
Landing
Nose
Landing
Nose
Nose
Gear
Parts and
Servicing
Servicing
Installation
Landing Gear Shimmy Damper Wear Tolerances
Inspection Procedures
Nose
and
General Information
Nose
Landing
Gear Strut Extension
Nose
Landing
Gear Wear Tolerances and
and Brake
System
5
55, 64
Landing
Gear and Brake
System
5
46
Inspection
Landing Gear
Cleaning
Procedures
Inspection
and
Nose
Landing
Gear Wheel
Nose
Landing
Gear Wheel Installation
Landing
Gear and Brake
System
5
46
Nose
Landing
Gear Wheel Removal
Landing
Gear and Brake
System
5
46
Nose
Landing
Gear Wheel
Mechanism
Landing
Gear and Brake
System
5
81
Nose
Landing
Gear Wheel Travel
Stop Adjustment
Landing
Gear and Brake
System
5
81
Heating
and
10
5
Steering
Nozzle, Heater Fuel Discharge
xxvi
Cooling System
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
or
System
Name
Section
Section Name
Page
Oil Cooler Vendor Publications
General Information
1
16
Oil Pressure
Power Plant
6
14
Oil Pressure Indicator Installation
Power Plant
6
5
Oil Pressure Removal
Power Plant
6
5
Oil Pressure Transmitter
Power Plant
6
5
Oil Pressure Transmitter Removal
Power Plant
6
5
Oil Radiator Installation
Power Plant
6
5
Oil Radiator Removal
Power Plant
6
5
Oil
System
Ground
2
6C
Oil
System Capacity
General Information
1
6
Oil
System
Filter
2
6A
Oil
System
Pressure
General Information
1
6
Oil
System
Pressure Fluctuation
Power Plant
6
5
Oil
System Screen Cleaning
2
7
Oil
System Temperature
Power Plant
6
5
Oil
Temperature, High
Power Plant
6
14
2
30
Adjustment
Ground
Replacement
Adjustment
Ground
Control Valve
Ground
Oils, Approved Engine
Handling
and
Servicing
Handling and Servicing
Handling
Handling
and
and
Servicing
Servicing
Openings, Fuselage
Access
(Model 55’s)
Airframe
3
4
Openings, Fuselage
Access
(Model 58)
Airframe
3
5
Openings, Wing
Access
(Model 55’s)
Airframe
3
6
Openings, Wing
Access
(Model 58)
Airframe
3
7
15
1
Overhaul and
Replacement
Schedule
Overhaul and
Replacement
Schedule
Overheat Thermostat, Cabin Heater
Heating and Cooling System
10
1,8
Overvoltage Relay
Electrical
13
12C, 13
Oxygen Cylinder
General Information
1
8
Oxygen Cylinder Retesting
Utility Systems
11
3
Utility Systems
11
2
Utility Systems
11
1
Oxygen
Mask
Cleaning
Oxygen System
E17
System
xxvii
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Section Name
Section
Oxygen System Cylinder
Utility Systems
11
3
Oxygen System Purging
Utility Systems
11
2
Oxygen System Recharging
Ground
2
7
Aircraft Finishes
12
4
Aircraft: Finishes
12
5
Aircraft Finishes
12
3
Aircraft Finishes
12
3
Aircraft Finishes
12
7
Aircraft Finishes
12
5
Aircraft Finishes
12
1
Paint, Urethane Primer
Aircraft Finishes
12
5
Paint, Urethane Topcoat
Aircraft Finishes
12
6
Painted Surfaces, Cleaning
Ground
2
11
Painting Aluminum
Aircraft Finishes
12
1
Paints, Enamel Topcoats
Aircraft Finishes
12
1
Paints, Epoxy
Aircraft Finishes
12
2
Paints, Magnesium Surfaces
Aircraft Finishes
12
7
Component
Paint
Item
System
or
Name
Epoxy Topcoat
Paint Pretreatment Primer for Urethane
Paint Pretreatment
Paint Primer,
(Wash) Primer, Epoxy
Epoxy
Magnesium
Paint Removal from
and
Cleaning (Urethane)
Paint
Stripping
Paint
Touch-Up Repair,
Parking
Brake
Parking Brake
Surfaces
Exterior
Handling
and
Servicing
Handling and Servicing
Page
and Brake
System
5
1
Landing
Gear and Brake
System
5
10
Periodic
Inspections
16
1
Periodic
Inspections
16
2
Adjustment
Landing Gear
Valve Overhaul
Periodic
Inspections
Periodic
Inspections,
1 GO-Hour
Periodic
Inspections,
Electric
Propeller
Deicer 166-Hour
Periodic
Inspections
16
16
Periodic
Inspections,
Electric
Propeller
Deicer 50-Hour
Periodic
Inspections
16
16
Pitot and Static Air
System
Utility Systems
11
74
Pitot and Static Air
System Cleaning
Utility Systems
11
75
Pitot and Static Air
System Inspection
Utility Systems
11
75, 78
Pitot and Static Air
System Testing
Utility Systems
11
75
Inspection
Utility Systems
11
75
Pitot
xxviii
System
Hose
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Pitot
Item
or
System
System Leakage
Plastic Windows,
Name
Test
Section Name
Section
Utility Systems
11
42
2
12A
Ground
Cleaning,
Handling
and
Servicing
Page
Pneumatic Pressure
System
Utility Systems
11
13
Pneumatic Pressure
System Adjustment
Utility Systems
11
15
Utility Systems
11
15
5
81
2
3
Pneumatic
System
Inline Filter
Inspection
System
Landing
Gear and Brake
Power, External
Ground
Handling
Power Plant
Power Plant
6
1
Power Plant Air Box
Power Plant
6
2
Power Plant Alternators
Electrical
13
9
Position
Light Adjustment, Landing
Power Plant Alternators
Power Plant
Gear
Servicing
Cleaning
and
Servicing
System
Ground
Handling
and
Servicing
2
8
Ground
Handling
and
Servicing
2
12
Power Plant Control Cables
Power Plant
6
3
Power Plant
Power Plant
6
2
Power Plant
6
3
Power Plant
6
8
Power Plant
6
4
13
13
Power Plant
6
4
Power Plant
6
5
Power Plant
6
5
Power Plant
6
8
Power Plant
6
5
2
8
Controls, Adjusting
Power Plant Cowl
Power Plant
Flap
Actuator
Rigging
Cylinder Differential Compression Check
Power Plant Fuel
Injector Pump
Electrical
Power Plant Generators
Power Plant Ground
Power Plant Idle Mixture
Power Plant Idle
and
Running
Warm-Up
Adjustment
Speed Adjustment
Breaker Point
System
Power Plant
Magneto
Power Plant
Magnetos Drop-Off
Power Plant
Magentos Servicing
Ground
Power Plant
Magnetos Timing
Power Plant
6
6
Power Plant
6
5
Power Plant
6
5
Power Plant
6
1
Power Plant
6
5
15
2
Power Plant Oil Pressure
Adjustment
Check
Adjustment
Power Plant Oil Pressure Fluctuation
Adjustment
Power Plant Oil Radiator
Power Plant Oil
Temperature Control
Power Plant Overhaul and
Valve
Replacement
Schedule
Handling
Overhaul and
and
Servicing
Replacement
Schedule
E17
xxix
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
Power Plant Removal and Installation
Power Plant
Servicing
Fuel
Power Plant
Servicing
Oil
Power Plant
Spark Plug
System
System
Chart
1
Ground
Handling and Servicing
2
6
Ground
Handling
and
Servicing
2
68
Ground
Handling
and
Servicing
2
13
13
15
6
9
10
15
Utility Systems
11
26
Utility Systems
11
30
Utility Systems
11
30
Utility Systems
11
15, 31
Ground
Measures
Precautionary Service
Pressure Deicer
6
System,
System
Power Plant
Troubleshooting
Surface
Page
Power Plant
Electrical
Power Plant Starter
Power Plant
Section
Section Name
System Name
Handling
and
Servicing
Pressure
Pump Installation
Pressure
Pump
Pressure
Regulator Adjustment,
Pressure
Regulator
Valve Installation
Utility Systems
11
31
Pressure
Regulator
Valve Removal
Utility Systems
11
30
1
9
5
13
Utility Systems
11
15
Utility Systems
11
15, 21
Utility Systems
11
15, 21
Utility Systems
11
21
Utility Systems
11
15
Utility Systems
11
19, 24
Utility Systems
11
13
Utility Systems
11
24
Primer, Epoxy
Aircraft Finishes
12
3
Primer Pretreatment, Urethane Paint
Aircraft Finishes
12
5
Primer, Urethane
Aircraft Finishes
12
5
Propeller
Propeller
7
1
Propeller
7
8
Propeller
7
8
Utility Systems
11
41
Utility Systems
11
41
Removal
Pressure Relief Valve
Pressure Switch
General Information
Adjustment
Adjustment, Landing
Pressure
System Adjustment
Pressure
System,
Pressure
System B-4, B-5,
Pressure
System
Pressure
System
Filter
Pressure
System
i H-14
Pressure
System,
Pressure
System
Propeller
Pneumatic
Landing
Gear
Basic
B-7
Autopilot
Deicer and B-4, 8-5, B-7
Autopilot
Inspection
Autopilot
Pneumatic
With Deicer and H-14
Autopilot
Accumulator
Propeller Adjustment
Windshield
Anti-icing
and Windshield
Anti-icing
Propeller and
Propeller
xxx
Maintenance
Gear and Brake
System
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Propeller
Item
or
System
Propeller Anti-icing
Propeller
Blade
Propeller
Deicer Brush
Propeller
Deicer
7
8
2
12
11
60, 62
i
7, 57
Utility Systems
11
59
Utility Systems
11
52, 55, 58,
Handling
and
Utility Systems
General Information
Replacement
Brush-to-Slip Ring Resistance,
Goodrich
Electric Timer Check
Propeller Deicer,
42
Ground
Propeller Cleaning
Deicer Boots
11
and
Servicing
Propeller
Repair
Propeller
8
Handling
Utility Systems
Boot Installation
Page
2
Ground
Service
System
Anti-leer Alcohol
Section
Section Name
Name
Servicing
65
Propeller Deicer, Goodrich
Utility Systems
11
52, 56
Propeller
Deicer Heat Test
Utility Systems
11
56, 58, 66
Propeller
Deicer
Utility Systems
11
69
Propeller
Electric Deicer Boot Installation, Goodrich
Utility Systems
11
60
Propeller
Electric Deicer Boot Installation,
Utility Systems
11
63
Utility Systems
11
60
Utility Systems
11
62
Utility Systems
11
68
Utility Systems
11
68
Utility Systems
11
55, 57
Utility Systems
11
59
Utility Systems
11
48, 53, 55,
Troubleshooting,
Propeller Electric Deicer
Propeller
Electric
McCauley
Boot Removal, Goodrich
McCauley
Electric Deicer Boot Removal,
Propeller Electric
McCauley
Deicer Brush Block Installation,
Propeller Electric
Deicer Brush Block Removal,
Propeller
Electric Deicer Brush Block
McCauley
Replacement,
Goodrich
Propeller
Electric Deicer Brush Block Resistance, Goodrich
Propeller Electric
Deicer Brush
Replacement
57, 66
Propeller
Electric Deicer Brush Wear Limits,
Propeller
Electric Deicer
Propeller
Electric Deicer, Goodrich
Propeller
Electric Deicer, Goodrich
Propeller
Electric Deicer,
Propeller
Electric Deicer Heat Test
Propeller
Electric Deicer
Inspection-i 00
Propeller
Electric Deicer
Inspection-50
E17
Continuity Check,
McCauley
Goodrich
(Hot Prop)
Goodyear
Hour
Hour
Utility Systems
11
66
Utility Systems
11
56, 59
Utility Systems
11
52, 56
Utility Systems
11
56
Utility Systems
11
48
Utility Systems
11
56, 58, 66
Periodic
Inspections
16
16
Periodic
Inspections
16
16
xxxi
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
System
or
Name
McCauley
Section Name
Section
Utility Systems
11
62
Page
Propeller
Electric Deicer,
Propeller
Electric Deicer Modular Brush
Replacement
Utility Systems
11
55, 57
Propeller
Electric Deicer Resistance Check, Goodrich
Utility Systems
11
59
Propeller
Electric Deicer
Slip Ring Alignment
Utility Systems
11
59, 68
Propeller
Electric Deicer
Slip Ring Cleaning, McCauley
Utility Systems
11
69
Propeller
Electric Deicer
Slip Ring
Installation
Utility Systems
11
59, 68
Deicer
Slip Ring Machining
Utility Systems
11
60, 69
Propeller
Electric Deicer
Slip Ring, McCauley
Utility Systems
11
68
Propeller
Electric Deicer
Slip Ring
Removal
Utility Systems
11
59, 68
Propeller
Electric Deicer
Slip Ring
Resistance
Utility Systems
11
59
Propeller
Electric
Utility Sysyem
11
69
Propeller
7
4
Propeller
7
3
Propeller
7
4
Propeller
7
3
General Information
1
6B
Propeller
7
3
Adjustment
Propeller
7
4
Propeller Electric
Troubleshooting
Propeller Feathering Adjustment
Propeller
Governor
Propeller
Governor
Propeller
Governor Installation
Propeller
Governor
Propeller
Governor Removal
Propeller High
Adjustment
Listing
RPM
Propeller
Installation
(Hartzell)
Propeller
7
2
Propeller
Installation
(McCauley)
Propeller
7
1
General Information
1
6
Propeller
7
4
Propeller
7
2
Propeller Removal (McCauley)
Propeller
7
1
Propeller Synchronizer
Propeller
7
5
Propeller Synchronizer Checks
Propeller
7
6
Propeller
7
7
Propeller
7
6
Propeller
7
9
Propeller
7
6
2
10
Propeller Listing
Propeller
Low RPM
Propeller
Removal
Adjustment
(Hartzell)
Propeller Synchronizer Flight
Check
Propeller Synchronizer Functional
Test
Propeller Synchronizer Troubleshooting
Propeller Synchronizer Wiring
Check
Propeller Unfeathering Accumulators
xxxii
Ground
Handling
and
Servicing
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
Section
Section Name
System Name
Page
General Information
1
15
Publications, Beechcraft
General Information
1
18
Publications, Supplementary
General information
1
15
Publications, Vendor
General Information
1
15
11
4, 30
6
4
Propeller
Pump
Pump,
Vendor Publications
Deicer
Fuel
Utility Systems
System
Power Plant
Injector
Pump Installation, Fuel
Boost
Pump Removal, Fuel Boost
Pump Servicing,
Fuel
System
8
20
Fuel
System
8
19
2
5
11
2
6
1
Ground
Heater Fuel
Handling
and
Servicing
Purging Oxygen System
Utility Systems
Radiator, Oil
Power Plant
Regulator Adjustment (Alternator)
Electrical
System
13
11
Regulator Adjustment (Generator)
Electrical
System
13
13
Electrical
System
13
30
11
26
5
81
Regulator,
Fuel Transmitter
Relay Adjustment,
Relay, Dynamic
Timer
or
Transducer
(Deicer)
Troubleshooting
Utility Systems
Landing
Brake
Gear and Brake
System
Relay, Overvoltage
Electrical
System
13
13
Relay Paralleling (Generator)
Electrical
System
13
15
Relief Valve
General Information
1
9
Adjustment,
Pressure
Relief Valve, Suction
Utility Systems
11
4
Replacement and Overhaul Schedule
Overhaul and Replacement
Schedule
15
1
Reservoir, Brake Fluid
General Information
1
8
2
4
Reservoir-Brake Fluid,
Servicing
Ground
Handling
and
Servicing
Reservoir Installation
Fuel
System
8
11
Reservoir Removal
Fuel
System
8
11
2
8
Reservoir
E17
Servicing,
Surface Deicer
Ground
Handling
and
Servicing
XXXIII
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
System
Control
Rigging Aileron
(TH-1389,
or
TH-1396 and
System
After)
Rigging Aileron Control System (Dual)
(TC-1 and After; TE-1 and After; TH-1
TH-1390 thru TH-1395)
Aileron Trim Tab
Rigging
Cowl
Rigging
Dual Control Arm Chain
Flap
Page
Flight Controls and Surfaces
4
15
and Surfaces
4
11
Controls and Surfaces
4
16
6
3
Flight Controls
thru TH-1388 and
Flight
Rigging
Section
Section Name
Name
Power Plant
Actuator
Flight
Controls and Surfaces
4
5
Rigging Elevator Control System (TC-1 and After; TE-1 and
After; TH-1 thru TH-1388 and TH-1390 thru iH-! 395)
Flight
Controls and Surfaces
4
26
Rigging Elevator Control System
(TH-1389, TH-1396 and After)
Flight
Controls and Surfaces
4
28
and Surfaces
4
11, 15
Rigging Flight Controls,
Aileron
Flight Controls
Rigging Flight Controls,
Elevator
Flight
Controls and Surfaces
4
26, 28
Rigging Flight Controls,
Rudder
Flight
Controls and Surfaces
4
49
6
4
4
49
Rigging
Mechanical Cowl Flap
Power Plant
Rigging
Rudder Control
Flight
Roller
Bearing
Lubrication
Roton Chair Locks
Rubber Seals,
System
Landing
Gear
Uplock
Servicing
Controls and Surfaces
Ground
Handling
and
Servicing
2
5
Ground
Handling
and
Servicing
2
10
12
8
Aircraft Finishes
Painting
Rudder and Tab
Flight Controls and Surfaces
4
49
Rudder and Trim Tab Travel
Flight Controls
and Surfaces
4
55
Rudder
Flight
Controls and Surfaces
4
69
Rudder Installation
Flight
Controls and Surfaces
4
49
Rudder Removal
Flight
Controls and Surfaces
4
49
Flight
Controls and Surfaces
4
49
Flight
Controls and Surfaces
4
55
1
14
and Surfaces
4
56
Controls and Surfaces
4
56
and Surfaces
4
56
Controls and Surfaces
4
58
Rudder
Balancing
Rigging
Rudder Travel
Rudder Travel
General Information
Gage
Rudder Trim Tab Actuator
Assembly
Rudder Trim Tab Actuator
Cleaning
Rudder Trim Tab Actuator
Disassembly
Rudder Trim Tab Free
xxxiv
and
Play Checking
Flight Controls
Inspection
Flight
Flight Controls
Flight
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
Rudder Trim Tab
or
System
Name
Flight
Rigging
Scheduled Maintenance Checks
Section
Section Name
Controls and Surfaces
Periodic
Inspections
Page
4
50
16
1
Ground
Handling
and
Servicing
2
7
Ground
Handling
and
Servicing
2
6
Ground
Handling
and
Servicing
2
31
Seals and Gasket Lubrication
Ground
Handling
and
Servicing
2
11
Seat Installation, Center
Airframe
3
33
Seat Installation, Front
Airframe
3
32
Seat Removal, Center
Airframe
3
33
Seat Removal, Front
Airframe
3
32
Seats-Back
Airframe
3
34
2
10
Airframe
3
34
Screen
Cleaning
Oil
Screen, Servicing Fuel Strainer
Sealing
Seats
Chart
Adjustment
Servicing
Seats- Vertical
Ground
Chair Locks
Adjusting
Handling
and
Servicing
Seats
5th and 6th Installation
Airframe
3
34
Seats
5th and 6th Removal
Airframe
3
34
Seats
5th and 6th
Stowage
Airframe
3
34
2
3
11
31
2
28
5
72
2
4
Ground
Servicing
Handling
Servicing
Air Filters
Utility Systems
Servicing
Chart
Ground
Handling
and
and
Servicing
Servicing
Brake
System
Shimmy Damper Assembly
Landing Gear and
Shimmy Damper Servicing
Ground Handling and Servicing
Gear
Shock Strut, Main
Landing
Shock Strut, Nose
Landing Gear
Shock Struts,
Servicing
and Brake
System
5
31, 41
Landing
Gear and Brake
System
5
55, 64
Ground
Handling
2
4
Landing Gear
and
Servicing
Slip Ring Alignment, Propeller
Electric Deicer
Utility Systems
11
59, 68
Slip Ring Machining, Propeller
Electric Deicer
Utility Systems
11
60, 69
Slip Ring, Propeller Electric Deicer, McCauley
Utility Systems
It
68
Solenoid Valve, Heater
Heating
10
4
E17
and
Cooling System
XXXV
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Item
Component
or
System
Section
Section Name
Name
1
6
2
13
Cooling System
10
5, 11
Cooling System
10
1,8
16
1
15
1
Spark Plug
General Information
Spark Plug Chart, Engine
Ground
Handling
Heating
and
Heating
and
Scheduled
Periodic
Inspections
Time Limits
Overhaul and
Spark Plug,
Heater
Spark Plug, Heater-Gap
Special
Conditions Caution Notice
Page
and
Servicing
Maintenance Checks
Special Conditions
Caution Notice
Replacement
Schedule
Stabilizer, Horizontal
Flight
Controls and Surfaces
4
61
Stabilizer, Vertical
Flight
Controls and Surfaces
4
59
Utility Systems
11
38
13
36
1
9
Utility Systems
11
40
Utility Systems
11
41
Utility Systems
11
40
Starter
Electrical
System
13
15
Starter Brushes
Electrical
System
13
15
Starter Lubrication
Electrical
System
13
15
Starter Overhaul
Electrical
System
13
15
Electrical
System
13
29
1
16
Installation
Stall
Strip
Stall
Warning Indicator, Troubleshooting
Electrical
Stall
Warning Switch
General Information
Stall
Warning
Stall
Warning Switch
Stall
Warning System Adjustment
Starter
Switch Heater
Heater Test
Troubleshooting
System
General Information
Starter Vendor Publications
Static Air and Pitot
System
Utility Systems
11
74
Static Air and Pitot
System Cleaning
Utility Systems
11
75
Static Air and Pitot
System
Utility Systems
11
75
Static Air and Pitot
System Inspection
Utility Systems
11
78
Static Air and Pitot
System Leakage
Utility Systems
11
75
Inspection
Utility Systems
11
88
Static Wick Installation
Utility Systems
11
88
Static Wick Removal
Utility Systems
11
88
Static Wicks
Utility Systems
11
88
Static Wick
xxxvi
Hose
Inspection
Test
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
Section
Section Name
Name
System
or
Page
Stations
Diagram (TC-1
and
After)
Airframe
3
1
Stations
Diagram (TE-1
and
After)
Airframe
3
2
Stations
Diagram (TH-I
and
After)
Airframe
3
3
Nose Wheel
Landing
Gear and Brake
5
81
Ground
Handling
2
2A
3
52
Steering Mechanism,
Storage
of
Airplane
and
System
Servicing
Airframe
Storm Windows
Strobe
Light,
Bullock Unit
System
Electrical
System
13
37
Strobe
Light,
Grimes Unit
System
Electrical
System
13
38
Strobe
Light
General Information
1
17
Strut Extension, Main
General Information
1
9
Strut Extension, Nose Gear
General Information
1
9
11
4
1
15
Utility Systems
11
26, 30
Vendor Publications
Suction Relief Valve Screen
Utility Systems
Cleaning
Supplementary Publications,
General Information
Vendor
Surface Deice
Surface Deicer
Cleaning
Utility Systems
11
35
Surface Deicer
Coating
Utility Systems
11
35
Surface Deicer Installation
Utility Systems
11
28, 33
Surface Deicer Removal
Utility Systems
11
28, 33
Surface Deicer
Repair
Utility Systems
11
26, 36
Surface Travel,
Flight
1
9
General Information
Control
Surfaces, Cleaning Exterior
Ground
Handling
and
Servicing
2
11
Surfaces, Cleaning Unpainted
Ground
Handling
and
Servicing
2
11
Surfaces, Control
Aileron
Flight Controls
and Surfaces
4
11
Surfaces, Control
Elevator
Flight
Controls and Surfaces
4
22
Surfaces, Control
Rudder
Flight
Controls and Surfaces
4
49
and Surfaces
4
73
Surfaces, Controls
Flight Controls
Flaps
Landing
Gear and Brake
System
5
82
Switch, Landing Gear Pressure
Landing
Gear and Brake
System
5
13
Switch, Landing Gear Safety
Landing
Gear and Brake
System
5
13
Switch, Stall Warning
General Information
1
9
Switches, Landing Gear Position Light Adjustment
Landing
5
82
Switch Adjustment, Throttle
E17
Warning
Horn
Gear and Brake
System
xxxvii
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
System
or
Name
Section
Section Name
Page
Propeller
7
6
Propeller
7
7
Propeller
7
6
Synchronizer, Propeller
Propeller
7
5
Synch ronizer Troubleshooting
Propeller
7
9
Propeller
7
6
4
2
6
5
10
1,8
Synchronizer
Checks
Synchronizer Flight
Synchronizer
Check
Functional Test
Synchronizer Wiring
Taper
Check
and Surfaces
Flight Controls
Pins
Temperature Control Valve, Oil
Power Plant
Thermostat, Cabin Overheat
Heating
and
Thread Lubricant Table
Ground
Handling
and
Servicing
2
14
and
Servicing
2
11
5
82
4
2
15
1
11
52, 55, 58,
Cooling System
Thread
Lubrication, Plumbing
Ground
Handling
Throttle
Warning Horn Switch Adjustment
Landing
Gear and Brake
Throw-Over Control Column
Time Limits
Maintenance Practices
Flight Controls
Overhaul and
System
and Surfaces
Replacement
Schedule
Timer, Propeller Electrical Deicer
Utility Systems
65
Relay Adjustment (Deicer)
Timer
Utility Systems
Timing Magnetos
General Information
Tire and Wheel
Landing
Repair
Gear and Brake
System
11
26
1
6
5
6
Tire Pressure
General Information
1
9
Tire Vendor Publications
General Information
1
17
Tires, Cleaning
Ground
Handling
Servicing
2
12
Servicing
Ground
Handling and Servicing
2
3
General Information
1
14
General Information
1
11
Torque Wrenches
General Information
1
13
Torques, Table of
General Information
1
10
Tires
Tools, Special
Torque Chart,
xxxviii
Flare
Fitting
and
E17
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
item
or
Section
Section Name
Name
System
Page
Torquing
Coarse Thread Series Bolts
General Information
1
12
Torquing
Fine Thread Series Bolts
General Information
1
12
2
1
8
18
Towing Airplane
Ground
Transducer
Fuel
or
Transmitter Removal
Handling
and
Servicing
System
Transmitter, Emergency Location
General Information
1
17
Transmitter
Fuel
8
18
13
41
8
16
or
Transducer Removal, Fuel
Transmitter Test,
Emergency
Locator
System
Electrical
System
Transmitters, Fuel Level
Fuel
Trim Tab
Flight
Controls and Surfaces
4
16
Flight
Controls and Surfaces
4
35
Flight
Controls and Surfaces
4
46
Flight
Controls and Surfaces
4
16
Flight Controls and Surfaces
4
33
Controls and Surfaces
4
20
Actuator, Aileron
Trim Tab Actuator, Elevator
Trim Tab
Trim
Actuator, Elevator
Electric
Tab, Aileron
Trim Tab, Elevator
System
Trim Tab Free
Play Check,
Aileron
Flight
Trim Tab Free
Play Check,
Elevator
Flight Controls
and Surfaces
4
41
Trim Tab Free
Play Check,
Rudder
Flight Controls
and Surfaces
4
58
Trim Tab Horn, Elevator
Flight
Controls and Surfaces
4
43
Trim Tab, Rudder
Flight
Controls and Surfaces
4
50
Troubleshooting Air-Conditioning
Heating
10
20
Troubleshooting
Alternators
Troubleshooting Battery
System
Troubleshooting
Brake
Troubleshooting
Cabin Heater
Control and Indicator
Troubleshooting
Fuel
Troubleshooting
Fuel Transmitter
Troubleshooting
Generators
Quantity
Indicator
or
Transducer
Regulator
Troubleshooting Ignition System
System
Troubleshooting Landing
Gear Electrical
Troubleshooting Landing
Gear Position Indicator
E17
Cooling System
Electrical
System
13
33
Electrical
System
13
27
5
86
10
6, 12
6
9
Landing
Gear and Brake
Heating
and
System
Cooling System
Power Plant
Troubleshooting Engine
Troubleshooting Flap
and
Electrical
System
13
35
Electrical
System
13
36
Electrical
System
13
30
Electrical
System
13
29
Electrical
System
13
33
5
86
13
34
Landing
Gear and Brake
Electrical
System
System
xxxix
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Item
Name
Section Name
Section
Troubleshooting Landing Lights
Electrical
System
13
36
Troubleshooting Navigation Lights
Electrical
System
13
36
11
69
7
9
Component
or
System
Troubleshooting Propeller Electric
Deicer
System
Troubleshooting Propeller Synchronizer
Troubleshooting
Stall
Troubleshooting
Starter
Troubleshooting Warning
Propeller
Indicator
Warning
Horn
Upholstery Cleaning Leather
Uplock
Roller
Bearing
Lubrication
Landing
Utility Systems
Gear
Page
Electrical
System
13
36
Electrical
System
13
29
Electrical
System
13
35
Ground
Handling
and
Servicing
2
12
Ground
Handling
and
Servicing
2
5
Aircraft Finishes
12
6
Urethane Paints
Colors
Urethane Paints
Pretreatment Primer
Aircraft Finishes
12
5
Urethane Paints
Primer
Aircraft Finishes
12
5
Urethane Paints
Stripping
Aircraft Finishes
12
5
List of
and
Cleaning
Utility Baggage Compartment
Door
Airframe
3
44
Utility Baggage Compartment
Door Removal and Installa-
Airframe
3
44
Door
Airframe
3
44
15
4
1
15
tion
Utility Baggage Compartment
Utility Systems
Overhaul and
Rigging
Replacement
Schedule
Overhaul and Replacement
Schedule
Vacuum
Pump Vendor Publications
General Information
Vacuum
System
Utility Systems
11
3
Vacuum
System Adjusting
Utility Systems
11
3
Vacuum
System
Utility Systems
11
4
Vacuum
System Suction Relief Valve
Utility Systems
11
4
Heating
10
19
Valve
xl
Gyro
Air Filter
Adjustment, Air-Conditioning Expansion
and
Cooling System
E17
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component
Item
or
System
Valve
Adjustment, Pressure Relief
Valve
Assembly,
Deicer
General Information
Utility Systems
System
Valve Control Cable, Fuel Selector
Fuel
Valve, Heater Solenoid
Heating
Valve
Section
Section Name
Name
Fuel
Inspection, Flapper
System
and
Cooling System
System
Page
1
9
11
9
8
15
10
4
8
18
6
5
5
10
11
4
Valve, Oil Temperature Control
Power Plant
Valve, Parking Brake
Landing
Valve, Suction Relief
Utility Systems
Valves, Installing the Fuel Selector
Fuel
System
8
15
Valves, Removing the Fuel Selector
Fuel
System
8
14
Vane, Stall Warning Adjustment
Utility Systems
11
40
8
18
1
15
10
1
8
19
and Surfaces
4
59
Velcro
Tape, Installed With
Fuel
Fuel Cells
Gear and Brake
System
Vendor Publications
General Information
Ventilation
Heating
Vent
System
Fuel
Line, External, Fuel Cell
System
and
Cooling System
System
Vertical Stabilizer
Flight Controls
Vertical Stabilizer Installation
Flight
Controls and Surfaces
4
59
Vertical Stabilizer Removal
Flight
Controls and Surfaces
4
59
1
16
5
82
13
35
1
9
11
40
Voltage Regulator
General Information
Vendor Publications
W
Warning
Horn Switch
Warning
Horn
Adjustment, Throttle
Troubleshooting
Warning Switch,
Wax
Application
Wedge Lights
Wheel and Brake
Wheel and Tire
Wheel
E17
Assembly
Repair
Bearing (Repack)
Gear and Brake
Electrical
System
System
General Information
Stall
Warning System Adjustment,
Landing
Stall
Utility Systems
Ground
Handling
Servicing
2
12A
Ground
Handling and Servicing
2
9
and
Landing
Gear and Brake
System
5
3
Landing
Gear and Brake
System
5
6
1
9
General Information
xli
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Item
Component
or
System
Wheel Throttle
Warning Horn Cam Adjustment
Wheel Throttle
Warning
Wheel Travel
Horn Microswitch
Adjustment
Stop Adjustment, Nose
Wheel Well and Nacelle
Section
Section Name
Name
Cleaning
Page
Landing
Gear and Brake
System
5
82
Landing
Gear and Brake
System
5
13
Landing
Gear and Brake
System
5
81
Ground
Handling
2
12
and
Servicing
Wheel Vendor Publications
General Information
1
16
Windows
Airframe
3
50
Windows, Aft
Airframe
3
55
Windows, Cabin Door
Airframe
3
54
Windows, Center
Airframe
3
55
Windows, Forward Left-Hand
Airframe
3
53
Windows, Storm
Airframe
3
52
Utility Systems
11
41
Utility Systems
11
41, 42
Windshield Deice Check
Utility Systems
11
47
Windshield Heater Functional Check
Utility Systems
11
48
Windshield Heater Installation
Utility Systems
11
45
Utility Systems
11
47
Utility Systems
11
47
Utility Systems
11
44
Windshield and
Windshield
Propeller Anti-icing
Maintenance
Anti-icing Systems
Windshield Heater
Relay Installation
Windshield Heater
Relay
Removal
Windshield Heater Removal
Windshield Heater
Temperature
Control Installation
Utility Systems
11
46
Windshield Heater
Temperature
Control Removal
Utility Systems
11
46
Windshield Installation
Airframe
3
51
Windshield Removal
Airframe
3
50
11
52
Windshield
Troubleshooting
Utility Systems
Wing
Access
Openings (Model 55’s)
Airframe
3
6
Wing
Access
Openings (Model 58)
Airframe
3
7
Wing
Installation
Airframe
3
11
Wing
Panel
Leading Edge
Installation
Airframe
3
10
Wing
Panel
Leading Edge
Removal
Airframe
3
10
Wing
Removal
Airframe
3
8
Airframe
3
8
Wing Tip
xlii
Installation
(Standard)
E17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ALPHABETICAL INDEX
Component Item
or
Wing Tip Installation,
Wing Tip
Removal
Wing Tip Removal,
System
Name
Wet
(Standardj
Wet
Section Name
Section
Page
Airframe
3
8
Airframe
3
8
Airframe
3
8
Wing Tip (Wet) Installation
Fuel
System
8
22
Wing Tip (Wet), Leak Check and Repair
Fuel
System
8
22
Fuel
System
8
22
Wing Tip (Wet) Removal
Fuel
System
8
22
Wings, Adjustment
Airframe
3
18
Bolt
Torque
General
1
10
Wrenches
General
1
14
Wiring Diagrams
14
2
Wiring Diagrams
Wiring Diagrams
14
1
Wrenches, Torque
General Information
1
13
Wing Tip (Wet),
Wings,
Wings, Bolt
Wiring Diagram
E17
Leak Test
Index
xliii
SECTION
GENERAL
INFORMATION
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
GENERAL INFORMATION
WARNING
IWARNINQ
Any maintenance requiring the disconnection
plumbing,
nent
being
electrical connectors
and reconnection of
flight
control cables,
wiring requires identification of each side of the compodisconnected to facilitate correct reassembly. At or prior to disassembly, comor
ponents should be color coded, tagged or properly identified in a way that it will be obvious
how to correctly reconnect the components. After reconnection of any component, remove
all identification tags. Check all associated systems for correct function prior to returning
the
airplane
to service.
The
organization of the Beech Baron Shop Manual has been planned with the intention of presenting the various
logical sequence for maximum convenience and minimum time required to locate the desired information.
The information in the manual is directed toward assisting the experienced mechanic with specialized and more
complex maintenance procedures while repetitive procedures are given less emphasis. Throughout the manual illustrations supplement the text and are located as closely as possible to the related discussion. The manual is divided into sixteen sections, with each section devoted to a specific system or major component. For convenience,
all information pertaining to a particular system (except servicing and wiring diagrams) may be found in one place
data in
in the manual.
To aid you in quickly locating the information you need, an alphabetical index contains multiple entries for each subject. Additional information which should prove most helpful includes troubleshooting guides, an overhaul and replacement schedule, based on past component performance; and a list of publications,’ comprising information on
various components of the Beech Baron.
I
If a question should arise concerning the care of your airplane, it is important to include the airplane serial number
in any correspondence. Airplane serials TO-i thru TC-1035 and TE-1 thru TE-451, the model designation placard
is attached to the bottom of the fuselage immediately forward of the tie-down lug. Airplane serials TC-1036 and after,
TE-452 and after, and TH-1 and after, the model designation placard is attached to the right side of the fuselage at
the inboard end of the flap. The placard is visible with the flaps lowered. The Beech Baron series is presently serialized
as
follows:
Model 55, serials TO-1 thru TC-190
Model A55, serials TC-191 thru TC-501, except TC-350 and TC-371
Model B55, serials TC-371, TC-502 and after
Model 055, serials TC-350, TE-1 thru TE-451
Model
D55, serials TE-452 thru TE-767
Model E55, serials TE-768 and after
Model 58, serials TH-I and after
The Models E55 and 58, except for wiring diagrams, are not in all cases denoted by serial effectivity throughout the
manual. However, information contained in the text for the Model D55 will apply to the Models E55 and 58 unless
otherwise noted.
1-1
E18
I
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
The
wiring diagram
except TH-598,
are
for the serials TC-1 thru TC-1935, except TC-1913; TE-1 thru TE-1063 and TH- I thru TH-647,
Shop Manual. The serial effectivity of each diagram
contained in Section 14 of this Beech Baron
is shown in the title of the
diagram.
Wiring Diagram Manual, part number 96-590011-15, for the wiring diagrams pertaining
airplane serials TC-1913, TC-1936 and after. Refer to the Beech Baron E55 and Baron 58
Wiring Diagram Manual, part number 96-590010-15, for the wiring diagrams pertaining to the Baron E55 airplane
serials TE-1064 and after and to the Baron 58 airplane serials TH-598, TH-648 and after.
Refer to the Beech Baron 855
to the Baron 855
NOTE
Service Publication reissues
manual, For information
the latest revision of
It shall be the
on
or
revisions
are
automatically provided
not
how to obtain reissues
or
Raytheon Aircraft Service Bulletin
responsibility
of the
referenced in this shop manual
to the holders of this
applicable to this manual,
2001 or subsequent revision.
revisions
No.
refer to
owner/operator to ensure that the latest revision of publications
utilized during operation, service, and maintenance of the air-
are
plane.
Raytheon
Aircraft
Company expressly
lete any part, part numbers, kits
notice.
or
reserves
the
right to supersede,
cancel and/or declare obso-
publication that may be referenced in this
manual without
I
prior
WARNING
I WARNIYO)
Use
only genuine Raytheon Aircraft Company
or
Raytheon Aircraft Company-approved
parts obtained from Raytheon Aircraft Company-approved sources, in connection with
maintenance and
Genuine
repair
Raytheon
of
Raytheon
Aircraft
Company airplanes.
Aircraft
Company parts are produced and inspected under rigorous prosuitability for use in Raytheon Aircraft Company airplane applications. Parts purchased from sources other than Raytheon Aircraft Company,
even though outwardly identical in appearance, may not have had the required tests and inspections performed, may be different in fabrication techniques and materials, and may be
dangerous when installed in an airplane.
cedures to insure airworthiness and
Salvaged airplane parts, reworked parts obtained from non-Raytheon Aircraft Company-approved sources, or parts, components or structural assemblies, the service history of which
is unknown or cannot be authenticated, may have been subjected to unacceptable stresses
or temperatures or have other hidden damage, not discernible through routine visual or
usual nondestructive testing techniques. This may render the part, component or structural
assembly, even though originally manufactured by Raytheon Aircraft Company, unsuitable
and unsafe for airplane use.
Raytheon Aircraft Company expressly disclaims any responsibility for malfunctions,
ures, damage or injury caused by use of non-Raytheon Aircraft Company parts.
Complete operating
instructions for the Beech Baron may be found in the
applicable
model Pilot’s
fail-
Operating
Hand-
book.
1-2
818
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
13. 77’
:.~’:5’:’:2’5’.’2.5’;’2’
o
::i
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~´•x;
.s´•.~iz
:Q~f.Y
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1~.
~W8ri
:5Si
Removed TC-1043 and
37.82’
:.x;:~:st;:´•:´•:
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r~.si555
~i
:´•:´•:´•::´•:´•f:~’
7B’I~DIA.
:´•:5~
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::´•~l:ilB::l:::::::::I:I:::il:
il´•-i-r´•´•´•-l´•-iT~5´•2
O
6" DIHEDRAL
i
9. 59’
---I
C-1043 and after
::::::::::~::::::s´•:::::::´•.
s:~´•:.:.:
55’´•:f´•f~;:
:li::::~
8
::a::~s
:´•:s
XI::2:
;:.´•.:;:.:;:.:;:r´•:´•:´•:´•:´•:´•:´•:i´•i:´•:´•:´•x´•:´•:
´•:-:;´•l:~l;:u:
~i3 :’75
’r::o:~
:I:´•i,;
Si~i i:R;X;i.s´•.2.´•.´•X´•X´•i
::j:I
"´•ii´•~.:
10 ~f
:~ns3n:i:i
1
7
10. 42"
7. 0’
1
26. 70’
prior
to
TC-502
27. 28’ TC-502 and after
Dimensions of
Airplane (TC-1
Figure 1-1
and
i i´•’:
::i iSiiiii~i
---1
i
THO~B
ss~74lnn
After)
1-3
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
15.94’
:´•:r´•:::´•.´•2.´•.s:::~:s,,,r--....
::s:5:-...
~s´•: .w~
O
.´•z.ss´•´•-
:´•:´•:´•:C´•:´•:´•:´•:´•~´•:´•:´•:i.
6
O
O
´•":´•:´•:´•x´•´•:´•x..´•.´•;;´•;;´•,´•;´•2:´•:´•:
::´•~;:´•:;f:;:;:;X::::::;:;
~j:i
~j
.´•zz.´•.´•~.2....´•.2.
.515-.555555iI~s.::::5::5´•:1:´•
97.82’
::s´•~::::::.:´•:-:.:.:.
:´•:´•:´•:´•:´•:´•:´•r:´•:´•:´•:´•:
::::::::::::::´•´•´•::´•:s´•:´•:
: ~: : I:´•::?´•:´•:´•::s´•:´•´•´•
I
´•:1:Sg:~::’:’:’:’:’’’’’’;’
´•.s´•.
´•´•´•´•´•´•t´•L´•´•´•´•´•´•
118.0"
:i:::i.::i::q;:.~8::::l::´•f:::::::::::::::´•:-:´•:´•:´•:´•:´•:´•:´•:s´•:´•:´•
i: .:.5:’. : :’:5:S.:5´•´•´•´•´•´•51´•5.´•1´•.´•´•´•
:f´•:
...~.´•´•´•5´•´•
I::~::I::%:::::l:i:"f’´•’’´•’’´•
.s´•t::::::::::::::::::::
.....´•...-...´•....2..:´•:
~a
70 DIHEDRAL
´•sqi~
.59’
:´•:i´•:C´•
1~3
,._,
´•-Z-´•-
c
x
.:..,.´•..:.´•.1.´•.:.´•.-,.
g~ prrt
I:
1
10" 32’
10"
8.05’
1
28.98’
TH~1B
991742AA
Dimensions of
Airplane (TE-1
Figure 1-2
thru
TE-300)
1-4
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
15.94’
.ssis´•~´•
´•:´•:´•:´•:´•:iiZ´•
o
oo:o~
O
:´•’´•’:´•’´•’’´•:´•:´•’´•’´•’´•1’-’´•7.:´•:´•
O
~t
r´•,.´•.´•.if´•.t-
..5´•.:;.:.s~z.´•....i2:´•
´•~´•:f´•f:
:t~
:5
22~
.:.:´•~´•:-:´•:´•:´•r.ss´•;;.;r.;r
i~
:5~555
37.82’
´•:´•::~´•:s: ´•:´•:´•::x´•:´•:´•:´•:´•:´•:´•:: ´•:´•:´•:´•:
iii
:::::::ISi85i’~´•:::::::::l:I:::I:::i:::i:
: .: :I:´•:´•:´•:´•:´•:´•:´•:´•:´•´•:´•:´•:: : ki: : : : ~: : :SY:i
:::::w::::
~78´•01(
a:f´•:........-..-.
DLA´•iEii::::::*:::::::
~i
....´•I´•´•
5
;:5´•:5:j
´•z:´•.:
:~´•::::::i
2´•´•´•5´•´•5
’’69 DIHEDRAL’RrP~wa
~Qq
W
´•;’::X::i:S:Si:´•:´•:´•:.:´•:´•:´•:´•X.:.:.
´•:´•:´•5:´•:´•:´•:.:´•I:´•:´•
.5’"1.1.’-’´•-´•-.’:::::::::R::
i:::,,:::,
il~liiiir
z.s´•.´•.´•.;´•.´•.´•.´•.´•.´•;´•.´•.
s´•::~
-´•;´•.´•;´•.´•;´•.´•;´•;´•:´•;´•.´•;´•:´•:´•:´•:´•;´•I´•´•´•:
1 i i i i isiri i I lbx.:
.f.,ii::Ii::iii:::::~:i´•:-niii:
i$:´•:´•
ji::: i
:s;
:i
;.zzt;:;5:;X..
:;I:
:´•x´•
f
2~.i
~´•:s´•:::
~:s
:::i:::~
~t
I
11.38"
8. 08’
TH9le
991143AA
28.98’
Dimensions of
Airplane (TE-301
Figure 1-3
and
After)
1-5
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
n
o
o\
o
IO
O
b
+OPTIONAL
LANDING
LIGHT, TH-B74
AND AFTER
L-- _I_I
15.94’
37.82’
77.8" DIAMETER PROPEUER USED ON
fn-1389 TH-1396 AND AFTER
n~,78.0" DIA.
6’ DIHEDRAL
I
esr-----I
r
10,43" PROPEUER GROUND CLEARANCE
ON Tn-1389, TH-1396 AND AFTER
’i’
,.L
I
rf;~e
10045’
9.93
i
I
29.78’
ss-so,lo
Dimensions of
Airplane (TH-1
Figure 1-4
and
After)
1-6
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
POWER PLANT
ENGINE
Model 55, A55 and B55, two Continental, 6
cylinder,
10-470-L fuel
injected engines
rated at 260
horsepower at
2625
rpm.
Model C55, 055, E55 and 58 (Serials TH-1 thru TH-1396 except
injected engines rated at 285 horsepower at 2700 rpm.
TH-1389)
two Continental 6
cylinder,
IO-520-C fuel
Model E55, serial TE-1143 and after, and Model 58, serial TH-973 thru TH-1395 except TH-1389, two Continental
cylinder, IO-520-CB engines are installed. These engines are identical to the IO-520-C engines except the
6
IO-520-CB
engine
has
a
stronger crankshaft and other changes related
Model 58 serials TH-1389, TH-1396 and after, two Continental 6
300
horsepower
to the
cylinder
stronger crankshaft.
IO-550-C fuel
injected engines
rated at
at 2700 rpm.
MAGNETO TIMING
18" to 20" before
center of number
one
19" to 21" before
center of number
one
21" to
center of number
one
top
top
23" before top
cylinder, (10-470)
cylinder, (10-520)
cylinder, (IO-550-C)
SPARK PLUGS
(Refer to Spark Plug Chart,
Champion GAP:
Section
2)
0.018 to 0.022
A.C. GAP: 0.018 to 0.022
FIRING ORDER
163254
NOTE
Number
one
cylinder
is the
rear
cylinder
on
the
right
hand side of the
engine.
OIL PRESSURE
30 to 60
psi
at 75" to 240" at
2,500 rpm.
OIL CAPACITY
12
quarts
1-7
E18
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLER
Two constant
following
The
speed full feathering.
is
a
list of
propellers
that
were
installed
on
PROPELLERS
PROPELLER PART
the Baron at the
BARON
factory.
(MODEL 855)
SERIAL EFFECTIVITY
INSTALLATION
MANUFACTURER
OPTIONAL
McCAULEY
STANDARD
MCCAULEY
OPTIONAL
McCAULEY
NUMBER
96-960006-603*1
TO-1 thru TC-472
78BFMO
TC-371, and TC-408
2AF36C39Pn8BFMO
TO-1 thru TC-472
ex.
ex.
TC-371, and TC-408
96-960006-604*n88F-0
TC-371, TC-408,TC-473
thru TC-1415
96-960007-61 4**n8FF-0
TC-874 thru TC-988
OPTIONAL
McCAU LEY
2AF34C55n8FF-0
TC-371,TC-408, TC-473
STANDARD
McCAULEY
TC-1416 and after
OPTIONAL
HARTZELL
TC-1416 and after
OPTIONAL
HARTZELL
TC-1416 and after
STANDARD
HARTZELL
BHCC2YF2CH/C8465-6
TC-1416 and after
OPTIONAL
HARTZELL
PHCA3VF2BF*n636DB
TC-502 and after
OPTIONAL
HARTZELL
96-960009-604**1
TC-973 and after
OPTIONAL
HARTZELL
PHCA3VF2BFn636D
TC-502 and after
STANDARD
HARTZELL
96-960006-610*
TC-1419 and after
OPTIONAL
HARTZELL
96-960022-603**
TC-1419 and after
OPTIONAL
HARTZELL
PHCC3YF2C7663-2R
TC-1419 and after
OPTIONAL
HARTZELL
PHCC3YF2F/
TC-1419 and after
OPTIONAL
HARTZELL
thru TC-1415
96-960006-608"/
PC8465-6, 08465-6
96-960022-601""/
PC8465-6, 08465-6
BHCC2YF2CHF/
FC8465-6
V7636D
FC7663-2R
*ANTI-ICE EQUIPPED
**DEICE EQUIPPED
1-8
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLERS
BARON
(MODEL C55, D55, E55)
SERIAL EFFECTIVITY
INSTALLATION
MANUFACTURER
96-960006-604*n8FF-0
TE-1 thru TE-848
OPTIONAL
McCAULEY
96-960006-606*n8F F-O
TE-I thru TE-848
OPTIONAL
McCAULEY
2AF34C55/78FF-0
TE-1 thru TE-848
STANDARD
McCAULEY
96-960008-610"/
TE-849 and after
OPTIONAL
McCAULEY
TE-849 and after
OPTIONAL
McCAULEY
BHCC2YF2CHF/
TE-849 thru TE-942
STANDARD
HARTZELL
FC84756
except TE-938
96-960008-601 */D3567/
TE-1 thru TE-848
OPTIONAL
McCAULEY
TE-I thru TE-860
OPTIONAL
McCAULEY
TE-1 thru TE-849
OPTIONAL
McCAULEY
TE-849 and after
OPTIONAL
HARTZELL
TE-861 and after
OPTIONAL
HARTZELL
TE-850 and after
OPTIONAL
HARTZELL
PROPELLER PART
NUMBER
FC8475-6
96-960021-609**1
FC8475-6
82NE6
96-96001 0-606**/D35671
82NB6
3AF32C75/82NB61
D3567
96-960008-611*1
FC7663-2R
96-960020-602"/
FC7663-2R
PHCC3YF2FI
FC7663-2R
1-9
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLERS
BARON
(MODEL 58)
SERIAL EFFECTIVITY
INSTALLATION
MANUFACTURER
96-960008-612*1
TH-1 thru TH-1395
OPTIONAL
HARTZELL
FC8475-6
except TH-1389
96-960021-61""/
TH-I thru TH-1395
OPTIONAL
HARTZELL
FC8475-6
except TH-1389
BHC-J2YF2CFI
TH-I thru TH-1395
STANDARD
HARTZELL
FO8475-6
except TH-1389
96-960008-613*1
TH-1 thru TH-1395
OPTIONAL
HARTZELL
FC8475-6
except TH-1389
58-960010-607"/
TH-1 thru TH-1395
OPTIONAL
HARTZELL
FC8475-6
except TH-1389
PHCJ3YF2F/FC7663-2R
TH-1 thru TH-1395
OPTIONAL
HARTZELL
STANDARD
McCAULEY
PROPELLER PART
NUMBER
except TH-1389
3AF32C512
82NEA-5
TH-1389, TH-1396 and
after
*ANTI-ICE EQUIPPED
**DEICE EQUIPPED
PROPELLER GOVERNORS MODEL 55, C55, D55, E55
PART NUMBER
EFFECTIVITY
210355
TO-1 thru TC-936
210438
TC-663, TC-937 thru TC-1398 and TC-1402
210666
TC-1399 thru TC-1709 except TC-1402
210714
TC-1710 and after
210439
TE-1 thru TE-851
210662
TE-852 thru TE-981 and TE-1710
210710
TE-981 and after except TE-1710
except TC-663
PROPELLER GOVERNORS MODEL 58
PART NUMBER
EFFECTIVITY
210662
TH-1 thru TH-466, TH-473, and TH-474
210710
TH-467 thru TH-472, TH-475 thru TH-1395
except TH-1389
96-380030-11
TH-1389, TH-1396 and after
1-10
Ef8
Raytheon Aircraft
SEECH BARON 55 AND 58 SHOP MANUAL
PROPELLER DEICER BRUSH REPLACEMENT
On BF Goodrich deicers
through
On
the
inspection
McCauley
replace
brushes when 15/32 inch maximum distance is measured
on a
wire inserted
hole in the brush support block.
deicers refer to BRUSH WEAR LIMITS
(McCauley)
in Section 11.
FUEL SYSTEM
FUEL GRADES: 100 LL
(Blue) preferred.
100
(Green)
FUEL CAPACITY
AIRPLANE SERIAL:
FUEL SELECTOR POSITIONS:
CAPACITIES:
TC-1 thru TC-1607; TE-1 thru
OFF-AUX-MAIN-CROSSFEED
112 Gallon
(106
TE-942, except TE-938
OFF-AUX-MAIN-CROSSFEED
TC-1 thru TC-1607; TE-I thru
TC-1608and after;TE-938,TE-943
OFF-ON-CROSSFEED
OFF-ON-CROSSFEED
TE-938, TE-943 and after;
Capacity System
Usable)
Gallon, Interconnected,
172
Gallon, Interconnected,
Capacity System
(166 Gallon Usable)
TH-1 and after
TH-669 and after With Wet
Wing
OFF-ON-CROSSFEED
200
Gallon, Interconnected,
Capacity System
(194 Gallon Usable)
Tips
FUEL PRESSURE ADJUSTMENT
Adjusting
142
Gallon
Capacity System
Usable)
Capacity System
(136 Gallon Usable)
and after; TH-I and after
See
142 Gallon
(136
TE-942, except TE-938
Gallon
Fuel
Pump,
(ENGINE-DRIVEN PUMP)
Power Plant Section 6.
MISCELLANEOUS
AIRCRAFT DIMENSIONS
OVERALL LENGTH
55, A55, 855..............................................
26.70’
prior to TC-502,
27.28’ TC-502 and after
C55, D55, E55
28.98’ TE-1 and after
58.................................................................
29.78’ TH-1 and after
1-11
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING SPAN
55, A55, 855, C55, D55, E551 and 58
37.82’
TAIL HEIGHT
55, A55, and B55.....................................................................
C55
9.6’
9.37’
.........___,
D55, E55.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9.22’
58.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .~
9.51’
TREAD WIDTH
55, A55, B55, C55, D55, E55, and 58
9.59’
PROPELLER DIAMETER
55, A55, B55, C55, D55, E55, and 58 prior
58
TH-1389, TH-1396
to TH-1396
except TH-1389
and after
78"
77"
PROPELLER GROUND CLEARANCE
55, A55, and 855.................................................................
10.42"
C55, TE-1 thru TE-300
10"
C55, TE-301 thru TE-451, D55 and E55
58 Prior to TH-1396
except TH-1389
11.38"
....................................9.93"
58 TH-1389, TH-1396 and after
10.43"
BRAKE FLUID RESERVOIR
Fill to 1 1/2 inch of the top with MIL-H-5606
on the dip stick.
or
MIL-H-83282
hydraulic fluid (Item 13,
Consumable Materials
Chart).
Maintain visible fluid level
BRAKE WEAR LIMITS
Refer to Section 5, LANDING GEAR AND
BRAKES, for brake
wear
limit dimensions.
OXYGEN CYLINDER
Fill
slowly
crease
to 1850 It50
3.5
psi
psi at 70" F. Increase the system 3.5 psi for every degree of temperature increase
degree decrease in temperature.
and de-
for every
1-12
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
STALL WARNING SWITCH
Adjust
to 7 to 9
m.p.h.
above
a
complete stall.
ADJUSTMENT OF PRESSURE RELIEF VAL VES
For
adjustment
of pressure relief valves refer to the PRESSURE SYSTEM ADJUSTMENT CHART in Section II.
MOTOR BRUSH REPLACEMENT GUIDE
NOTE
On
be
airplanes TC-2003 and after, TE-1084 and after, and
replaced any time it needs overhauled for any reason.
Flap............................................
5/16 inch minimum
L.G. Retract
5/16 inch minimum
Heater Blower............................
3/16 inch minimum
Combustion Air Blower
3/16 inch minimum
Alternator
Slip Ring....................
Propeller Slip Ring.....................
TH-773 and after, the
flap
motor should
On Condition
On Condition
FLIGHT CONTROL SURFACE TRA VEL
Approach,
Flap............................................
O" Full
Aileron
20" -´•1"
UP,
20" ~1" DOWN
Aileron Tab
10" ~1"
UP,
10" +1" DOWN
Rudder.......................................
25" +1"
RIGHT, 25" +1" LEFT
Rudder Tab................................
25" +1"
RIGHT, 25" ~1" LEFT
Elevator
30" +1"
UP, 15" ~1" DOWN
Elevator Tab
10" +1"
UP, 23" ~1" DOWN
Up,
15" +1"
30"
0" -2" Full Down
1-13
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
SERVICE
TIRE PRESSURES
NOSE WHEEL TIRE
TC-I thru TC-501
(Except TC-350, TC-371)
TC-350, TC-371, TC-502
50
and after
psi
48 to 52
psi
TE-1 thru TE-300
48 to 52
psi
TE-301 and
55 to 60
psi
TH-1 and after
55 to 60
psi
MAIN WHEEL TIRES
TC-1 thru TC-501
TC-371, TC-502
(Except TC-371)
50
and after
psi
50 to 54
psi
TE-1 thru TE-451
55 to 60
psi
TE-452 and
52 to 56
psi
TH-1 and after
52 to 56
psi
TC-2092 and after, TE-1114 and after, TH-873 and after
(That are equipped with Cleveland Heavy Duty Brakes)
50 to 54
psi
MAIN GEAR STRUT EXTENSION
3 inches
NOSE GEAR STRUT EXTENSION
4 1/2 inches
.........___.
TC-I and after; TE-1 thru TE-300
3 3/16 to 3 7/16 inches.TE-301 thru TE-405
3 1/2 to 3 3/4 inches..... TE-406 and after
WHEEL BEARINGS
(REPACK)
100 hours
BATTERY
(SINGLE
24 VOLT OR TWO 12
VOLT)
100 hours
PNEUMATIC FILTERS/SCREENS
Inlet filter
(Pressure Pump).
..........____..
Replace every
300 hours
or sooner
if conditions warrant.
1-14
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
VACUUM FILTERS/SCREENS
Central Air Filter
Gyro
(Gyro Instruments)....... Replace every
Instrument Air Filters......................
Suction Relief Screen
Replace
300 hours
or sooner
if conditions warrant.
every 300 hours
or sooner
if conditions warrant.
I
100 hours
FUEL SCREENS/STRAINERS
Fuel
System
Screens and Strainers....... 100 hours
or sooner
if conditions warrant.
OIL SYSTEM
Oil Filter
100 hours
Oil Pressure Screen
Clean in solvent every 25 hours
Oil
25 hours
Change....................
(at
oil
(TC-1
change)
and
after),
100 hours
(TE-1
and
after),
100 hours
(TH-1 and after)
NOTE
New
engines
with Rustband oil
NO later than 25 hours
or
(MIL-C-6529 Type 2)
should have the oil
6 months. The oil filter MUST be
changed
changed
at 20 hours but
when the break-in oil with Rust-
band is removed.
1-15
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TABLE OF TORQUES
ENGINE MOUNTING
Engine
Mount Bracket Bolts and Nuts
Engine
Shock Mount Bolts and Nuts
(At Firewall)
400 ~15
inch-pounds
325 +25
inch-pounds (TC-1 and after),
inch-pounds (TE-1 and after; TH-1
475 +25
Engine Bonding Jumper (At Starter)
190
200
inch-pounds
155
175
inch-pounds
and
after)
COMPONENT ATTACHING BRACKETS TO
ENGINE
Engine Sump Bolts (At
Brackets)
Control Cable
Attaching
Mixture Lever Nut
100
(do
Throttle Lever Nut
100
(do
inch-pounds with
110
not
110
not
lever in idle cutoff
position
torque against lever stop)
inch-pounds
with lever in closed
position
torque against lever stop)
ENGINE BAFFLE ATTACHING BOLTS AND NUTS
10-32
40
1/4-20
80 +5
inch-pounds
50 rt5
inch-pounds
1/4-20
(Rocker
Box Cover
Only)
inch-pounds
1/4-28
100 f10
3/8-24
370
REB3N OR F34-14M ROD END NUTS
(Used
MAX.
inch-pounds
390
inch-pounds
on
throttle, mixture and prop controls)
AN316-4R
30 +5
inch-pounds
AN310-3
15 ~t5
inch-pounds
Propeller torque
in
inch-pounds
Hartzell
McCauley
Propeller 10-470 Engines
720 to 840
660 to 780
Propeller
840 to 960
660 to 780
10-520
Engines
Propeller 10-550 Engines
960 to 1020
WING MOUNTING
See Section 3 Airframe.
HORIZONTAL AND VERTICAL STABILIZER
Front
Spar Mounting
Bolts
(Horizontal Stabilizer)
85
100
inch-pounds (Prior to TC-2457 except
225 inch-pounds (All TE and TH
TC-350)
Serials and TC-350, TC-2457 and after)
200
Rear
Spar Mounting
Bolts
(Horizontal Stabilizer)
85
Front
Spar Mounting
Bolts
(Vertical Stabilizer)
160
100
inch-pounds (All TC,
190
TE
inch-pounds (All TC,
TE
TH
Serials)
TH
Serials)
1-16
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TABLE OF TORQUES
Spar Mounting Bolts and Upper
Mounting Bolts (Vertical Stabilizer)
Front
Aft
Spar
(CONTINUED)
190
160
inch-pounds (Prior to TC-2457,
Prior to
TE-1202, Prior to TH-1484), 330 360 inch-pounds
(TC-2457 and after, TE-1202 and after, TH-1484 and
after)
Lower Aft
Spar Mounting
Elevator Horn
Bolts
Hinge Mounting
(Vertical Stabilizer)
inch-pounds (Prior to TC-2457, Prior to
TE-1202, Prior to TH-1484), 85 100 inch-pounds
(TC-2457 and after, TE-1 202 and afte r, TH-1484 and
after)
70
50
inch-pounds (Prior to TC-2457, Prior to
to TH-1484), 30 40 inch-pounds
Maximum of 70 inch-pounds if necessary to align
cotter pin holes. (TC-2457 and after, TE-1202 and
Bolts
70
50
TE-1202, Prior
after, TH-1484 and after)
WING SURFACE CONTROLS
inch-pounds
Push Rod to Bell Crank
30
60
Bell Crank to Structure
50
100
inch-pounds
AIR CONDITIONER
Drive
Pulley
700
800
inch-pounds
180
200
inch-pounds
LANDING GEAR
Main
Landing Gear
Brace Bolts
Cross Arm to Barrel Attach Bolts
Main
Landing
Gear
80
Hinge Bolts
250
Brake Back Plate Attach Bolts
(For
Cleveland
Heavy Duty
Brakes
inch-pounds
690
inch-pounds
inch-pounds
80
90
inch-pounds
only)
WHEEL HALF ASSEMBLIES
(All
TC and TE
serials)
Main Wheel
Assembly
140
Nose Wheel
Assembly
83
(All
TH
inch-pounds
serials)
Main Wheel
Assembly
150
Nose Wheel
Assembly
90
inch-pounds
inch-pounds
NOTE:
Be
sure to
tighten
all wheel attach bolts
evenly to
make certain the
assembly is
not
warped.
1-17
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TORQUING FINE THREAD SERIES BOLTS LOADED IN SMEAR
TORQUE LIMITS RECOMMENDED FOR INSTALLATION
MAXIMUM ALLOWABLE TIGHTENING
(INCH-POUNDS)
SIZE
TORQUE
COLUMN 1
MS20365&
AN310 Nuts
MS21042
I Dry-Film
Lub. Nut
.1640-36
8-36
12-15
.1900-32
10-32
20-15
.2500-28
1/4-28
.3125-24
COLUMN 2
MS20364
AN320
Nuts
MS21245
Dry-Film
Lub. Nut
(INCH-POUNDS)
COLUMN 3
MS20365
AN310
Nuts
MS21042
Dry-Film
Lub. Nut
COLUMN 4
MS20364
AN320
Nuts
MS21245
Dry-Film
Lub. Nut
7-9
20
15-19
12-15
40
30
25
50-70
37-47
30-40
100
70
60
5/16-24
100-140
56-78
60-85
225
135
140
.3750-24
3/8-24
160-190
72-108
95-110
390
200
240
.4375-20
7/16-20
450-500
270-300
840
500
.5000-20
1/2-20
480-690
290-410
210-230
1100
660
415
.5625-18
9/16-18
800-1000
480-600
310-430
1600
960
660
.6250-18
5/8-18
1100-1300
660-780
485-605
2400
1400
1060
.7500-16
3/4-16
2300-2500
1300-1500
1090-1250
5000
3000
2500
.8750-14
7/8-14
2500-3000
1800-2400
1640-2100
7000
4200
3740
1-14
3700-5500
2200-3300
10000
6000
11/8-12
5000-7000
3000-4200
15000
9000
11/4-12
9000-11000
5400-6600
25000
15000
12
NOTE:
The above values
apply to
Class 3 threads, cadmium plates and nonlubricated (except as noted).
The above torque values may be used as a guide when specific
torques are not called out within this manual.
1-18
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TORQUING COARSE THREAD SERIES BOLTS LOADED IN SMEAR
MAXIMUM ALLOWABLE
TORQUE LIMITS RECOMMENDED FOR INSTALLATION
TIGHTENING
(INCH-POUNDS)
TORQUE
MS20365
AN310
MS20364
AN320
COLUMN 4
COLUMN 3
COLUMN 2
COLUMN 1
SIZE
(INCH-POUNDS)
MS20365
INuts
AN310
MS20364
AN320
Nuts
Nuts
Nuts
8-32
12-15
7-9
20
12
10-24
20-25
12-15
35
21
1/4-20
40-50
25-30
75
45
5/16-18
80-90
48-55
160
100
3/8-16
160-185
95-110
275
170
7/1 6-14
235-255
140-155
475
280
1/2-13
400-480
240-290
880
520
9/16-12
500-700
300-420
1100
650
5/8-11
700-900
420-540
1500
900
3/4-10
1150-1600
700-950
2500
1500
7/8-9
2200-3000
1300-1800
4600
2700
1-8
3700-5000
2200-3000
7600
4500
11/8-8
5500-6500
3300-4000
12000
7200
11/4-8
6500-8000
4000-5000
16000
10000
NOTE:
threads, cadmium plates and nonlubricated (except as noted).
The above torque values may be used as a guide when specific torques are not called out within this manual.
The above values
apply
to Class 3
1-19
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
FLARE FITTING TORQUE CHART
TORQUE
TUBING
ALUMINUM
ALLOY
OD
TUBING FLARE
INCHES
AND10061 OR AND10078
MINIMUM
MAXIMUM
INCH POUND
STEEL TUBING FLARE
HOSE END FITTING AND
AND10061
HOSE ASSEMBLIES
MINIMUM
MAXIMUM
MINIMUM
MAXIMUM
90
100
70
100
1/8
3/16
1/4
40
65
135
150
70
120
5/16
60
80
180
200
85
180
3/8
75
125
270
300
100
250
112
150
250
450
500
210
420
5/8
200
350
650
700
300
480
3/4
300
500
900
1000
500
850
1
500
700
1200
1400
700
1150
11/4
600
900
11/2
600
900
13/4
750
1050
2
800
1100
1- 20
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TORQUE WRENCHES
When
a
torque wrench and adapter is used, (Figure 1-5) compensation
will
must be made for the extra
must be calculated before the wrench is used. To
readings
actually give the torques specified,
New indicator
use
Original wrench length x specified toraue
length of wrench adapter
the
following
figure
leverage gained.
readings which
I
the desired lower
formula:
desired
reading
example:
Desired reading
Length of torque
Adapter length
Torque
D
L
A
T
wrench
D=?
33 inches
L
A=llinches
5,000 inch-pounds
T
33
5.000 =165000
x
An
method of
acceptable
scale to
to an
a
3750
inch-pounds
44
11
33
checking
conventional flex
imaginary
line
or
the torque, if
a
extending from the
not available, (Figure 1-6) is to attach a spring I
adapter. Force should be applied in a direction perpendicular
bolt through the spring scale attaching point.
torque wrench is
"T" handle inserted in
an
center of the
pounds (scale reading) required to obtain the specified torque, divide the torque in
in inches between the center of the bolt and the scale attaching point. For example, if
distance
the
inch-pounds by
the specified torque, is 5,000 inch-pounds and the distance is 25 inches a pull of 200 pounds must be applied. Un-
To calculate the force in
less torque values
are
specified
as
wet
(lubricated), bolts to be torqued must
establishing the torque values may
erwise loss of normal friction allowed for
When
a
torque wrench adapter is used, the length of the adapter
wrench and
a
value calculated for the
particular
be clean and free of all lubricants; othresult in
over
torquing
of the bolt.
length of the flex or’7" handle
typical example in finding a desired
must be added to the
combination. The
following
is
a
value.
Effective
length of
flex
or
"T"
Handle wrench...........................
12 inches
length of adapter........................
Total length........
3 inches
Desired torque
on
2000 inch-pounds
15 inches
bolt............... 2000
133.3
inch-pounds
pounds (scale reading)
15 inches
1-21
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TOTAL LENGTA
L
ii
THO1B
991744AA
Torque Wrench and Adapter
Figure 1-5
(LB)
90"
TOIEQUE
(IN. LB)
TOTAL LENGTH
THO1B
991 745AA
Determining Torque by spring
Figure 1-6
Scale
1-22
818
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
SPECIAL TOOLS
I
1
I
I
O
50-590090
AILERON TAB TRAVEL GAGE
t~gj’
B
8
\\I
MODEL 300 OR 300 100 SERVICE JACK
HOISTING SLING
HOISTING SLING ADAPTER
SERVICE JACK ADAPTER
95 590016 1
95 590017
TK1518
9$-590017
MAIN WHEEL JACK
ADAPTER 35 590006
F’ROPELLER WRENCH
TQSOA
USED WITH P N
1
45 590080
or
810 96-630000-1
RUDDER TAB TRAVEL GAGE
932 3500000 1
TS1222-3
LOWER FORWARD WING BOLT WRENCH
50-590014
LOWER FORWARD WING NUT TORQUE WRENCH ADAPTER
TS1222-3
(9116
1D1 590020 1 FUEL SUMP DRAIN WRENCH
(WET WING TIP)
inch
hex)
or
(Yi inch hex]
TS1222-4
UPPER FORWARD WING BOLT WRENCH
TS1171-2
UPPER FORWARD WING NUT TORQUE WRENCH ADAPTER
(TC-1
thru
(FOR
INTERNAL WRENCHING
(FOR
EXTERNAL WRENCHING
NUT)
TC-2358. TE-I thru TE-1182, TH-1 thru TH-1192)
810-2 96-524000
TS1176-2
UPPER FORWARD WING NUT TORQUE WRENCH ADAPTER
TC-2359 and after, TE-1183 and after, TH-1193 and
T51222-4
FLAP TRAVEL GAGE
NUT)
after)
UPPER AFT WING BOLT WRENCH
TS1171-1
or
50-590013
UPPER AFT WING NUT TORQUE WRENCH ADAPTER
ADAPTER KIT MODEL 300
30 IS TO BE USED WITH
THE MODEL 300 SERVICE JACK
TK1817
WHEN USED
ON SERIAL TE 301 AND AFTER AND TH 1 AND
922-4
LOWER AFT WING BOLT WRENCH
TS1171-2
LOWER AFT WING NUT TORQUE WRENCH ADAPTER
(808 INTERNAL WRENCHING NUT)
LOWER AFT WING NUT TORQUE WRENCH ADAPTER
(FOR
AFTER
810-96524000
RUDDER TRAVEL GAGE
or
TS1176-10
EXTERNAL WRENCHING
NUT)
50-590013
151222 3
TS1171 1
TS1171 2
1
TS1222
4
TK1817 922-4
50 590014
TS 1176-2
TS1176-10
810 1 95524000RH
810 13513502578LH
810 13513502579RH
AILERON TRAVEL GAGE
I
810´•1 95524000LH
ELEVATOR AND ELEVATOR TAB TRAVEL GAGE
6~-176
Speciai Tools
Figure 1-7
1-23
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
1-24
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
SUPPLER/IENTARY PUBLICA TIONS
is a list of publications providing servicing, overhaul and parts information on various components of the
Beech Baron which you may obtain to supplement the Shop Manual. In most instances, you should obtain the publications directly from the manufacturer or his distributor. Raytheon supplementary publications, are available from
Raytheon Aircraft Company Technical Support. Those which are available are listed in the current Publications Price
Following
List. Since
and
As
a
wide
variety of radio equipment
servicing manuals
publications
on
with each set, radio
is available and because radio manufacturers
publications
I
normally supply parts
have not been included in the list.
additional components become available,
they
will be added to this list of
publications.
I
SUPPLIER PUBLICA TIONS
ENGINE
NOTE
following engine manuals are not available through Raytheon Aircraft Company. Please order
publications for the engine from Teledyne Continental Motors, Aircraft Products, Mobile, Ala-
I
The
all
bama.
Operations and Service Maintenance Instructions Form
Motors Corporation, Box 90, Mobile, Alabama 36601.
No. X-30024, 10-470
Maintenance and Overhaul Manual Form No. X-30022, 10-470
Engine Series, Teledyne Continental
Engine Series, Teledyne
Continental Motors
Corpo-
ration, Box 90, Mobile, Alabama 36601.
Parts
Catalog
Form No.
X-30023A, 10-470 Engine Series, Teledyne Continental Motors Corporation, Box 90, Mo-
bile, Alabama 36601.
Operating and Field Maintenance Manual Form
Corporation, Box 90, Mobile, Alabama 36601.
No. X-30041, 10-520
Maintenance and Overhaul Manual Form No. X-30039A, 10-520
poration,
Parts
Engine Series, Teledyne Continental
Engine Series, Teledyne
Motors
Continental Motors Cor-
Box 90, Mobile, Alabama 36601.
Catalog
Form No. X-30040A, 10-520
Engine Series, Teledyne
Continental Motors
Corporation,
Box 90, Mo-
bile, Alabama 36601.
Tips
on
Engine Care, Teledyne
Continental Motors Aircraft Products Division, Box 90, Mobile, Alabama 36601.
FUEL SYSTEM
Description, Operation, Adjustment
Injection System Manuals, Form No.
Engine Series, Teledyne Continental Motors Corporation, Box 90, Mo-
and Service Instructions Continental Fuel
X-30048 and X-30049, 10-470 and 10-520
bile, Alabama 36601.
Fuel
Injection
Manual Form No. X-30052, 10-470 and 10-520
Engine Series, Teledyne
Continental Motors
Corpo-
ration, Box 90, Mobile, Alabama 36601.
Overhaul Manual for Electric Boost
Northridge
Pumps, P/N
4613-00-1 and 4404-00-1, Dukes Inc., 9060 Winnetka Ave.,
CA 91324.
1-25
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLER
Owner’s Manual 206C for Hartzell Propeller PHC-A3XF and PHC-A3VF Series, Optional Three Blade
Hartzell Propeller Inc., 350 Washington Avenue, Piqua, Ohio 45356.
Propeller,
Overhaul Instructions 114B for Hartzell Propeller PHC-A3 ()with Errata Sheet No. 2 Optional Three Blade
Hartzell Propeller Inc., 350 Washington Avenue, Piqua, Ohio 45356.
Propeller,
Maintenance Handbook for Constant
Governor
Company,
Owners Manual No. 651030 for
Corporation,
Speed Hydraulic Propeller Governor Type CSSA,
Street, Rockford, Illinois 61101.
No. 330014, Woodward
5001 North Second
McCauley 2AF34C, 2AF36C
Dayton, Ohio 45417.
and 3AF32C Series
Propellers, McCauley
Industrial
Parker at Howell Ave.,
Spinner Assembly
Maintenance Instruction Guide, Part No.
3000 Hartzell
Propeller, Inc., Piqua, Ohio.
VACUUM PUMP
Overhaul Manual G-455 Series,
Wichita, Kansas 67201.
Am Vacuum
Pumps,
(includes parts list),
Carruth Laboratories, Garwin Division, 1326 South Walnut,
Overhaul and Maintenance Instructions with Illustrated Parts
400 Enterprise Street, Byron, Ohio.
Breakdown, Publication No.
TM66-1, The Aro Corporation,
BATTERY
Operation
and Service ´•Manual, GET-3593A, For Nickel-Cadmium Batteries, General Electric
Products Section, P.O. Box 114, Gainesville, Florida 32601.
Service Manual, GSM-1277, for Gill Aircraft Batteries,
Service Manual CB12-9, for the Concorde Aircraft
Covina CA 91790.
Teledyne Battery Products, Redlands,
Battery,
Concorde
Battery Corp.,
Company, Battery
California.
2009 San Bernadino Rd. West
GENERATORS
DR 324S Test
Group
Specifications, Delco-Remy Division,
93G Parts List,
General Motors
Delco-Remy Division, General
Motors
Corporation, Detroit, Michigan.
Corporation, Detroit, Michigan.
ALTERNATOR
lG-262, Service Bulletin, Test and Maintenance of "Delcotrons" Delco-Remy Division, General Motors Corporation,
Detroit, Michigan.
Group
88L Parts List,
Equipment Lists,
Delco-Remy Division,
General Motors
Corporation, Detroit, Michigan.
Service Parts Lists, Technical Data, Publication No. OE-A1, Prestolite
Overhaul Manual Form X30531 Continental-Crittenden
craft Products, Mobile, Alabama.
100
Company, Toledo,
Ampere Alternator, Teledyne
Ohio.
Continental Motors, Air-
1- 26
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
VOLTAGE REGULATOR
DR 3248 Test
Group 6K
Specifications, Delco-Remy Division,
Parts List,
Delco-Remy Division,
General Motors
General Motors
Corporation, Detroit, Michigan.
Corporation, Detroit, Michigan.
lR-273, Service Bulletin, Test and Adjustments of Transistor Regulators, Delco-Remy Division, General Motors Corporation, Detroit, Michigan.
OIL COOLER
Test
Specifications,
P/N 8256732, Harrison Radiator Division, General Motors
Corporation, Buffalo,
Overhaul Instructions, Service Bulletin HES 77E, Harrison-Radiator Division, General Motors
New York.
Corporation, Buffalo,
New York.
STARTER
Group 55A Cranking Motor Parts List, Delco-Remy Division, General Motors Corporation, Detroit, Michigan.
MAGNETO
Installation, Operation and Maintenance Instructions, Bendix S-1200 Series Magnetos Form L-609B, Scintilla Division, Bendix Aviation Corporation, Sherman Avenue, Sidney, New York.
Service Parts List, Bendix S-1200 Series
Sherman Avenue, Sidney, New York.
Magnetos,
Form L-608, Scintilla Division, Bendix Aviation
Corporation,
Installation, Maintenance and Operation Instructions, Bendix S-200 Series Magnetos, Form L-526, Scintilla Division,
Corporation, Sherman Avenue, Sidney, New York.
Bendix Aviation
Service Parts List, Bendix S-200 Series
Sherman Avenue, Sidney, New York.
Catalog
Magnetos,
Form L528-2, Scintilla Division, Bendix Aviation
and Service Manual, Form 1012, 600 Series, Slick Electro Inc., 530 Blackhawk Park Avenue,
Corporation,
Rockford,
Illinois 61101.
WHEELS, BRAKES AND TIRES
Maintenance Instructions for
Company,
1210 Massillon
Goodyear
6.50-8 Brake
Assembly 9532475,
P/N AP-125,
Goodyear
Tire and Rubber
Road, Akron, Ohio.
Overhaul Information for Brake Shuttle Valve, Publication No. 74456, Hoof Products Co., 6543 South Laramie Avenue,
Chicago 38,
Illinois.
Overhaul Information for Brake Shuttle Valve, Publication No. 23595, Paramount Machine Co.,4122 Kent Road,
Stow, Ohio.
HEATER
Maintenance Instructions for Janitrol D83 A28, Aircraft Heater, P/N 30657, Janitrol Aero Division, Midland-Ross
Corporation, 4200 Surface Road, Columbus, Ohio.
Maintenance Instructions for Janitrol 81D94-3 Aircraft Heater, P/N 98D19-1, Janitrol Aero Division, Midland-Ross
Corporation, 4200 Surface Road, Columbus, Ohio.
1-27
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
Maintenance Instructions for Janitrol 11C30 Aircraft Heater Ignition Unit, No. 24C54, Janitrol Aero
Division, Midland-Ross Corporation, 4200 Surface Road, Columbus, Ohio.
Maintenance Instructions for Janitrol 87D24-5 Aircraft Heater Ignition, P/N 93D00-1, Janitrol Aero
Division, MidCorporation, 4200 Surface Road, Columbus, Ohio.
land-Ross
HEATER AIR BLOWER
Overhaul Instructions Vane Axial for Part No. M4862H1A, with Motor M2916V,
East Dyer Road, Santa Ana, California, 92705.
Dynamic
Air
Engineering Inc.,
620
LIGHTWEIGHT DEICER BOOTS
Installation Manual for
Lightweight
Reservoir
Type
Pneumatic
Deicing Systems
for Beech Aircraft,
Report
No.
58-138, B. F. Goodrich Company, 448 South Main, Akron, Ohio.
Maintenance and
South Main,
Repair
of
Lightweight
Reservoir
Assembly, Report
No.
61-137, B. F. Goodrich Company, 448
Akron, Ohio.
AUTOPILOT
B-5
Flight Control System
Tulsa, Oklahoma, 74151.
B-5 Automatic
Flight
Ground and
Control
Flight
Check Procedures, P/N 3952, Brittain Industries Inc., P.O. Box 51370,
System, Maintenance Manual,
P/N 3950, Brittain industries Inc., P.O. Box 51370,
Tulsa, Oklahoma, 74151.
Brittain Industries B-VII
or B-7 Flight Control
P.O. Box 51370, Tulsa, Oklahoma, 74151.
Troubleshooting Manual,
P/N 3960, B-7
System Flight
Autopilot System,
Procedures Manual, P/N 3959, Brittain Industries, Inc.,
Brittain Industries Inc., P.O. Box 51370, Tulsa, Okla-
homa, 74151.
STROBE LIGHT
Instruction and Service Manual for
Airguard Anti-collision Beacon,
Publication Number: 50082. Bullock
Corp., Pomona, California.
Magnetics
AIR CONDITIONER COMPRESSOR
Service Manual. I.D. 160717, Abacus Air
Conditioning Compressor
Models 506-507, Abacus International, Dallas,
Texas.
EMERGENCY LOCATOR TRANSMITTER
Operating
Instructions for Model CIR-10
Collins/Communications
Operating
Emergency Locator Transmitter System,
Components Corporation, Costa Mesa, California.
Instructions for Model CIR-11
Emergency
Locator Transmitter
Transmitter P/N iR70-17,
System, Transmitter
P/N TR70-13, Col-
lins/Communications Components Corporation, Costa Mesa, California.
Owners Manual, Installation and Pilot’s Guide P/N 037160601 for the Narco FLT 10
Narco Avionics, Division of Narco Scientific Industries, Fort
Emergency Locator Transmitter,
Washington, Pennsylvania.
1-28
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
RAYTHEON AIRCRAFT BEECH PUBLICATIONS
Maintenance Instructions for Beech
Propeller
Model 2AF34C Series, 2AF36C Series and 3AF32C75 Series,
630901, Raytheon Aircraft Company.
Owner’s Manual for Beech
Propeller
Model 2AF34C Series and 2AF36C Series 651030-1,
Raytheon
Aircraft Com-
pany.
92-30582 Maintenance Instructions for
Goodyear
Nose Wheel and Tire.
92-30583 Maintenance Instructions for
Goodyear
Main Wheels, Brakes and Tires.
98-35061 Maintenance Instructions for Cleveland Nose and Main Wheels and Brakes.
98-33857 Maintenance Instructions and Parts Breakdown for Oeco
Voltage Regulator.
98-36235 Installation, Maintenance and Illustrated Parts Breakdown for Oeco
98-37515D
Safety
Voltage Regulator
P/N 60-389017-1.
Information Booklet.
H-14 AUTOPILOT
98-34350 H-14
13033F
Operators’
Adaptive
Manual.
Maintenance Manual.
92-301038 Overhaul Instructions for BG274B2, BG274C1 and BG274C2
Computer.
92-302048 Overhaul Instructions for CG21781, CG217B2 and CG217B3
Flight
92-30105 Overhaul Instructions for CG136A1
Heading
Controller.
Selector.
92-301068 Overhaul Instructions for MG113A1, MG113A2, MG113A3 and MG113A4 Actuator and SG28A1,
SG28A3 Switch.
92-30107A1 Overhaul Instructions for PGS1A1 Altitude Control.
98-32523 Overhaul Instructions for MG112A1 and MG112A2 Pitch Trim Actuator.
92-30229 Overhaul Instructions for GG205A3, GG205A4 Turn and Bank Indicator
92-30230 Overhaul Instructions for
DG103A1,
81
Gyro.
Adapter.
92-304118 Overhaul Instructions for GG201A1 and 0020181 Vertical
Gyro.
1-29
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
SUPPLEMENTARY RAYTHEON AIRCRAFT PUBLICATIONS
92-304128 Overhaul Instructions for GG202A1 and GG202B1 Directional
92-30413 Overhaul Instructions for GG301B1 Vertical
Gyro.
Gyro.
92-30414 Overhaul Instructions for GG302B1 Directional
92-30614 Overhaul Instructions for AIM 200
I
Gyro.
Gyro Direction
Indicator.
92-30615 Overhaul Instructions for AIM 300 Horizon Reference Indicator.
98-32839 Overhaul Instructions for CG417B1, CG417B2
130376A B-4 New-matic
Operating Servicing
Flight Controller,
Instructions
130409 New-matic Maintenance Instructions.
888-34679 B-5
Operator’s
98-35850 Electronics
Manual.
Components Maintenance
Manual and Parts Breakdown.
RAYTHEON AIRCRAFT NEW-MATIC AUTOPILOT
I
11807 B-4 and B-4A Maintenance and Service Manual.
92-402 New-Matic Pilot
130332
Dynertial
Operating
Instructions.
Pitch Control Pilot
Operating
Instructions.
1-30
E18
SECTION
GROUND HANDLING
AND SERVICING
~feechcraft
BARON 55 AND 58
SHOP MANUAL
GROUND HANDLING
I
ground handling of the airplane to
avoid unnecessary damage. The following procedures
are provided to reduce the possibility of ground damExercise
care
in the
Do not exceed the structural Ilmltatlons of the Model 3001ack. It Is recommended that no airplane weighing
over 5,000 pounds be lacked on the
Danalr/Tronair Model 300 lack, and
that a similar Ilmltatlon be observed
on older models of this lack. Make
sure’ that the safety bar is engaged at
age,
TOWING
Attach the hand tow bar to the two
lugs
on
the
WARNING
nose
gear lower torque knee,
jack.
Do not
surfaces.
on
the
horizontal stabilizer to raise the nose
wheel off the ground. When towing,
observe the turn limits to prevent damage to the nose gear. When removing
the tow bar, use care to avoid damaging
the grease fittings. DO NOT attempt to
tow the airplane backwards by the tail
tiedown
CAUTION
Never tow or taxi with
or
a
500
b.
Screw the
jack fitting or eyebolt adapter
jack point.
c.
taxiing
strut can cause severe
rear
into the
pletely
a
of
com-
rear
jack under the airplane up against the
jack points, and position the rear clevis
attachment of the rear fitting/eyebolt adapter.
Position the
two forward
for
Install the
safety pin
I
deflated
damage.
in the rear
jack point fittingl
and clevis.
flat strut. Even
with
weight on the tray at the rear
pounds is recommended.
jack extension;
eyebolt
f"2~
towing
Place a suitable
a.
d.
brief
the
the
plate
lug.
on
on
move
Model 300 jack.
propeller or control
Do not place any weight on the
push
Is raised
time the
airplane
y
n
aa
Do not
any airplane
CAUTION
w´•w~WARNING
I
The rear lack point eyebolt safety pin
must be Installed to reduce the possi-
JACKING
blllty of the airplane nosing
the lack.
over on
CAUTION
1 o,,,,l
CAUTION
Prior to jacking the airplane, ensure thaf
an unbalanced condition does not exist
Fuel should be distributed evenly in both
wings to prevent an unbalanced condition which could cause the airplane to be
Do not attach the rear support arm on
the jack extension to the tail of the airplane at this time. Damage to the airplane and the jack could result if the jack
is raised or lowered with the jack extension rear support arm attached to the tail
unstable while on the jacks. Older versions of the Bonanza three point jack,
which do not have a movable aftjacking
adapter attach point, should not be used
to
of the
e.
JACKING WITH MODEL 300 JACK
WITH TRONAIR UC~ENSION
The
jacking procedures for a
with
515
a
airplane.
jack Baron airplanes
(EQUIPPED
KIT)
i.
Model 300
Tronair Extension Kit P/N 4013
jack equipped
are as
follows:
Raise the
jack safety
jack to the desired height
Attach the
rear
in the tail of the
ensure a
and install the
lock.
stable
support
arm
to the tie-down
airplane, securing
attach point.
the
sliding
fitting
tube to
2-1
~Sleechcraft
BARON 55 AND 58
SHOP MANUAL
To lower the
g.
rear
the
support
arm
jack safety
jack,
disconnect the jack extension
from the airplane before removing
WARNING
lock.
The rear lack
T~
Never raise
or
lower the
point eyebolt safety pin
posslairplane nosing over on
must be installed to reduce the
jack
blllty of
the jack.
with the
jack
extension rear support
attached to the airplane.
the
arm
CAUTION
i caunoN-(
Do not attach the
h.
Remove the aft
removal of the
jack point fitting/eyebolt after
Model 300 jack from under the air-
Raise the
jack safety
JACKING WITH MODEL 300 JACK
The
the tail of the
e.
plane.
TRONAIR UC~ENSION
jacking procedures
equipped
has not been
are as
(WITHOUT
A
KIT)
for
f.
Model 300
a
jack
which
jack to the
Attach the
Tronair Extension Kit
follows:
tube to
rear
airplane
support weight to
at this time.
desired
height
and install the
lock.
ensure
support tube to the tie-down fitting
airplane. Secure the adjustable sliding
a stable point for the airplane.
rear
in the tail of the
a
with
I
g. To lower the jack, disconnect the rear support
tube from the airplane before removing the jack safety
lock.
I
ARNING
CAUTION
Do not exceed the structural Ilmltatlons of the Model 300 lack. It Is recommended that no airplane weighing
over
5,000 pounds be jacked
on
Never raise or lower the airplane on a
Model 300 jack with a rear support tube/
weight assembly attached.
the
h.
Danalrrrronalr Model 300 lack, and
that
Remove the aft jack point
removal of the Model 300
similar Ilmltatlon be observed
on older models of this lack. Make
sure that the safety bar Is engaged at
any time the airplane Is raised on the
~ack. Do not move any airplane on a
luodei 300 lack.
a
sure a
suitable
weight
a.
is available to anchor
the tail of the airplane to be jacked. The use of a tail
tiedown device with a suitable weight 500 pounds
such as P/N 35-590021 embedded in a movable
concrete-filled barrel
b.
Screwthe
c.
Position the
or
equivalent.
Attach
two forward
plate
d.
under the
Install the
safety pin
and clevis.
airplane up against the
position the rear clevis
rear fitting/eyebolt adapter.
and
for attachment of the
eyebolt
2-2
jack
jack points,
com-
in the rear
jack point fitting/
suitable
weight to anchor the tail of the
jacked. P/N35-590021 embedded in a
concrete-filled barrel or equivalent may be
a
to be
Used.
b.
Position the two
tripod jacks under the forward
proper clearance from all movable
components and gear doors.
jack points. Ensure
c.
rearjackfitting or eyebolt adapter
into
the
rear jack point.
pletely
air-
JACKING WITH (2) TRIPOD JACKS, TRONAIR
MODEL 100 OR EQUIVALENT
movable
Make
after
plane.
airplane
a.
fitting/eyebolt
jack from under the
Simultaneously jack
jacking
both jacks to ensure a level
required clearance is obtained
gear operation of both the nose and main
action until the
for normal
Sears.
d.
Make sure the
immediately
e.
after
jack safety
jacking.
locks
are
engaged
To lower the
locks and
airplane, disengage the jack safety
simultaneously lower both jacks.
515
aeechcraft
BARON 55 AND 58
SHOP MANUAL
Remove the
f.
the two
weight assembly after removing
moving the airplane.
rear
tripod jacks
I
and before
I
w~-´•´•
ARNING
ANCHORING AND MOORING
Before rotating the propeller blades,
make certain the magneto/start
PROVISIONS
Three
and
provided, one
bumper. To moor
mooring eyes
one
are
in the tail
in each
the
wing
airplane,
chock the wheels fore and aft, install the control locks
and tie-down with a nylon cord or chain of sufficient
length
at each
point.
Avoid
line, which will pull up the
the
rear
that wind will
cre-
overtightening
nose so
higher lift on the wings. If bad weather
pated, it is advisable to nose the airplane
ate
is antici-
into the
wind.
primary objective of these measures
corrosion
and damage from exposure
prevent
elements. The three types of storage are:
7 to 30
Flyable storage
a.
b.
Temporarystorage
-31
c.
Indefinite storage
91
are
to
to the
days.
are
Each
are
in the
and the mixture
In the IDLE CUT-OFF
clear while
seven
shall be rotated
If at the end of
thirty days
the
airplane
will not
be removed from storage, the engine shall be started
and run. The preferred method will be to fly the air-
plane
for
thirty minutes.
If
flying
the
airplane
is
imprac-
tical, a ground run shall be made of thirty minutes
duration, and up to, but not exceeding normal oil temperatures.
Fuel Cells. Fill the fuel cells to
c.
capacity
to mini-
mite fuel vapor.
to90days.
days
controls
OFF, throttles
position,
days during flyable storage, the
propeller
by hand without running the
After
the
engine.
rotating
engine six revolutions, stop
the propeller 45" to 90" from its previous position.
4.
5.
The
use.
are
position. Always stand
turning the propeller.
STORAGE
The storage procedures are intended to protect the
airplane from deterioration while the airplane is not in
switches
CLOSED
d.
and after.
Flight
Control Surfaces. Lock the
flight
control
sur-
faces with internal locks.
FLYABLE STORAGE
7 TO 30 DAYS
e.
a.
and
Mooring
Place the
1.
airplane
in a
hangar.
airplane cannot be placed in a hangar,
securely at the three tie-down points provided on the airplane. Do not use hemp or manila
rope. It is recommended that a tail support be used to
compress the nose strut which will reduce the wing
angle of attack. Attach a line to the nose gear.
If the
2.
Operate
the
engine
until the oil temperature
supply from
reaches the normal range. Drain the oil
the sump as completely as possible and
drain
replace
the
plug.
Pitot Tube. Install
g.
Windshield and Windows.
This will mix with normal oil, is suitable as a
provide protection against corrosion.
Run the
engine
speed between 1000
perature and cylinder
operating range.
515
tube
airplane securely
covers.
Close all windows.
2.
It is recommended that
covers
be installed
the windshield and windows.
a´•
at least five minutes at a
and 1200 rpm with the oil temhead temperature in the normal
Remove all covers, tape and control locks. Clean
the
airplane and give it a thorough inspection, particularry wheel wells, flaps and control openings.
Drain the MlL-C-6529
Chart)
(3, Consumable
Materials
warm-up. Fill with engine oil
Consumable Materials Chart) before flight.
c.
lubricant and will
3.
pitot
the
1.
over
b.
Fill the sump to the full mark on the oil dipstick
with MIL-C-6529 Type II oil (3, Consumable Materials
2.
Chart).
ground
PREPARATION FOR SERVICE
Engine
1.
Static
f.
tie it down
b.
Grounding.
effectively.
after
ground
Preflight the airplane.
TEMPORARY STORAGE
a.
(2,
31 TO 90 DAYS
Mooring
1.
Place the
airplane
in a
hangar.
2-2A
~S3eechcraft
BARON 55 AND 58
SHOP MANUAL
If the
2.
tie it down
vided
on
airplane cannot be placed in a hangar,
securely at the three tie-down points pro-
the
airplane.
Do not
use
hemp
or
manila
f.
Pitot Tube. Install
g.
Windshield and Windows.
1.
rope. It is recommended that a tail support be used to
compress the nose strut which will reduce the wing
angle
b.
of attack. Attach
a
line to the
nose
Engine
i.
Operate the engine until the oil temperature
reaches the normal range. Drain the oil supply from
the sump as completely as possible and replace the
drain
1.
Remove
from the
airplane
practices.
2.
Clean the
and ELT
airplane
battery
Chart).
present.
This will mix with normal oil, is suitable
provide protection against
Run the
as a
corrosion.
at least five minutes at a
engine
speed between 1000 and 1200 rpm with the oil temperature and cylinder head temperature in the normal
operating range.
Remove the top and bottom spark plugs and
atomize-spray preservative oil (3, Consumable Materials Chart) through the upper spark plug hole of each
4.
as
each
the crankshaft with
5.
inder interior, move the noule of the spray gun from
the top to the bottom of the cylinder.
6.
Reinstall the
b.
With the bottom
spark plugs removed, hand-turn
propeller several revolutions to clear excess preservative oil, then reinstall the spark plugs.
3.
Seal all engine openings exposed to the
atmosphere using suitable plugs, or nonhygroscopic
tape, and attach red streamers at each point,
place
Affix
with
tag to the propeller in a conspicuous
the following notation on the tag: "DO NOT
a
TURN PROPELLER
10.
Seal the
ENGINE PRESERVED".
propeller
blade
spinner
cutouts with
c.
Fuel Cells. Fill the fuel cells to
Flight Control Surfaces.
capacity
to mini-
e.
Lockthe
Grounding. Static ground
effectively.
2-25
flight
test.
INDEFINITE STORAGE
a.
Mooring
Placethe
airplane inahangar.
2.
If the airplane cannot be placed in a hangar,
tie it down securely at the three tie-down points provided
on the airplane. Do not use hemp or manila
rope. It is recommended that a tail support be used to
compress the nose strut which will reduce the wing
angle of attack. Attach a line to the nose gear.
b.
Engine
1.
Operate the engine until the oil temperature
’eaches the normal range. Drain the oil supply from
the sump as completely as possible and replace the
drain plug.
Fillthesumptothefull markontheoildipstick
Type ii oil (3, Consumable Materials
Chart).
This will mix with normal oil, is suitable as a
provide protection against corrosion.
lubricant and will
flight control
sur-
faces with internal locks.
and
and
with MIL-C-6529
mite fuel vapor,
d.
P’eflight the airplane
2.
tape.
(3,
Consumable Materials
Chart)
ground warm-up. Fill with engine oil (2,
Co"sumable Materials Chart) before flight.
1.
tube.
9.
D’ain the MIL-C-6529
after
spark plugs.
7.
Apply preservative to the engine interior by
I spraying preservative oil (3, Consumable Materials
Chart) (approximately 2 ounces) through the oil filler
battery cable termiacid that may be
the
d´•
Stop
in the down
box and
battery
Remove all covers, tape and control locks. Clean
and give it a thorough inspection, particularry wheel wells, flaps and control openings.
airplane
Respray each cylinder without rotating the
crankshaft. To thoroughly cover all surfaces of the cyl-
the crankshaft
piston
battery
a.
the
C´•
with the
batteries and ELT
Locator
PREPARATION FOR SERVICE
position. Rotate
pair of cylinders is sprayed.
no piston at the top position.
cylinder
(Emergency
and store in accordance with stan-
"als to neutralize any
3.
I
It is recommended that covers be installed
the windshield and windows.
Fill the sump to the full mark on the oil dipstick
2.
with MIL-C-6529 Type II oil (3, Consumable Materials
lubricant and will
covers.
Close all windows.
h. Airplane batteries
T’a"smitter) battery.
dard
plug.
tube
2.
over
gear.
pitot
the
airplane securely
3.
R,, the engine at least five minutes at a
speed between 1000 and 1200 rpm with the oil temperature and cylinder head temperature in the normal
operating range.
515
aeechcraft
BARON 55 AND 58
SHOP MANUAL
Remove the top and bottom
4.
I
spark plugs and
atomize spray preservative oil (3, Consumable Materials Chart) through the upper spark plug hole of each
with the
cylinder
the crankshaft
piston
each
as
the crankshaft with
Stop
position. Rotate
of
cylinders is sprayed.
pair
no piston at the top position.
e.
Seats. Install
f´•
shaft should
wrapped
with
propellers
airplane. Each propeller
be coated with preservative oil and
moisture proof material and tape.
Goodyear fuel cells, manufactured
(Construction No. ETC-39 or
ETC-67) are installed, no preservative
procedures are necessary when the cell
If
after 1961
Install protex plugs in each of the spark plug
sure that each protex plug is blue in
is to be empty for
7.
6.
plug
a bag of desiccant in the exhaust pipes
openings with moisture-resistant tape.
engine
in the breather and
Wraptheengineswith moisture-proof material
tape after the desiccant bags have been installed.
10.
Attach
a
red streamer to each
engine where bags
of desiccant
are
place on
placed. Attach
streamers outside of the sealed area with
to
prevent wicking
11.
The
plugs
color indicates
an
safety
of moisture into the sealed
red
wire
area.
should be changed as soon as their
unsafe condition of storage. If the
cylinder bores should be resprayed with
mixture every six months or
corrosion-preventative
more frequently if bore inspection indicates corrosion
has started earlier than six months. Replace all desiccant and protex plugs. Before spraying, the engine
shall be inspected for corrosion as follows: Inspect the
interior of at least one cylinder on each engine through
the spark plug holes. If the cylinder shows the start of
oil
rust, spray the cylinder with corrosion-preventative
The
and turn the prop over five or six turns, then respray.
Remove at least one rocker box cover from each engine and
c.
inspect the valve
Clean the
bug accumulation.
2.
propellers
to remove dirt, oil and
Use water and
wrap with
tape.
Drain the fuel cells and coat the cells with
light engine
oil
let stand empty,
as
Flight
2.
h.
or
a
fill the cells every ten
applicable.
Control Surfaces
Lock with internal locks.
1.
Apply a thin
Chart).
coat of grease
(11,
Consumable
Materials
2.
i.
j.
a
a
soft brush.
preservative
oil and
Install Covers.
Windshield and\l\lindows.
1.
Close all windows.
2.
Install
covers over
windshields and windows.
Landing Gear
Clean the brakes and apply a coating of
1.
primer (24, Consumable Materials Chart) to the brake
discs.
protective
Touch up all spots where the
from the wheels.
paint
has been
3. After mooring, cover or wrap the wheels with
barrier material and secure with tape.
4.
aS
material to
Check the air pressure
periodically
and inflate
"ecessary.
5.
for
I
PitotTube.
2.
moisture-proof material and tape. If the
have been removed, coat all parts with a
exclude dust, then
thin coat
Lubricate all flight control surfaces hinge pins,
1.
bearings, bellcranks, chains, control rods and quadrants and coat lightly with corrosion-preventative
compound (49, Consumable Materials Chart)
a
propellers
preservative oil,
515
g.
or
chipped
Coat the blades with
wrap with
days
a
mechanism.
Propellers
1.
1.
thin coat of
the
dehydrator plugs have changed color in one-half or
more of the cylinders, all desiccant material on the
engine should be replaced.
12.
the walls must be coated with
of light engine oil.
by inserting protex
clamping in place.
breathers
9.
and
atmosphere except
lines in the airplane. Goodyear fuel cells
manufactured prior to 1961 and Uniroyal
fuel cells must be filled every ten days or
spark
Place
Seal the
indefinite time. The
opened to the
for the normal vent
an
fuel cells should not be
holes, making
and seal the
covers.
NOTE
and the
color when installed. Protect and support the
plug leads with AN4060-1 protectors,
protective
Fuel Cells.
be removed from the
engines
6.
Grounding. Static ground the airplane securely
effectively.
in the down
It is recommended that the
5.
and
d.
It is advisable that unserviceable tires be used
prolonged storage.
2-2C
I
aeet~hcraft
BARON 55 AND 58
SHOP MANUAL
6.
Coat the exposed surfaces of the shock strut
pistons and nose gear shimmy damper piston with
preservative hydraulic fluid (40, Consumable Materials
Chart)
and protect with barrier material.
c.
Drain the MIL-C-6529
d. Rotate the propellers to clear
oil from the cylinders.
e.
Reinstall the spark
Do not apply corrosion preventative to
the exposed surfaces of the landing gear
strut
piston
I
to the extended
or
surfaces of the
k.
Airplane batteries
Transmitter) battery.
polished
hydraulic cylinders.
and ELT
(Emergency
2.
Clean the
battery
box and
battery
secure with
tape.
Seats. Install protective
Landing Lights.
secure with tape,
n.
Stall
o.
1.
ARNING
wU´•I.,
Warning
ner.
Cover with barrier material and
Unit.
Remove and store according to standard
Tape
g.
Give the
inspect
and
airplane
flight test.
a
thorough cleaning, visually
CONTROL LOCK ~TC-I THRU TC-1436; TE-I
THRU TE-B59; AND TH-1 THRU TH-222)
NOTE
connections.
q. Airframe. Cover static ports and all openings with
barrier material and secure with tape to exclude rain,
sun and foreign material,
r.
Avionics. Clean and cover any equipment sensitive to dust or moisture and take any additional
precautions recommended by manufacturer of such
equipment,
s.
Hydraulic System. Pill the hydraulic reservoir to
the operational level and inspect the system for leaks,
then repair as necessary prior to storage.
PREPARATION FOR SERVICE
Remove all covers, tape and tags from the air-
plane,
b.
Remove the cylinder protex plugs, all paper tape
and
dehydrating agent
2-2D
I
covers.
The rudder pedals must be in the aft
position before the rudder lock can be
installed.
p. Loose Tools and Equipment. Remove the loose
tools and equipment and store in a dry room,
a.
battery.
Rotate the propellers by hand through all
compresSio"S of the engines to check for liquid lock. Reinstall
the cowling and start the engines in the normal man-
practices.
2.
and
preservative
f.
Instrument Panel. Cover with barrier material and
m.
plugs
excess
battery cable termiacid that may be
present.
i.
ground
mixture controls are In the IDLE CUTOFF position. Always stand In the
clear while turning the propellers.
practices.
nals to neutralize any
II oil after
Before rotation of the propeller
blades, ascertain that the magneto/
start switches are OFF, the throttles
are In the CLOSED position, and the
Locator
i.
Remove airplane batteries and ELT battery
from the airplane and store in accordance with stan-
dard
Type
warm-up. Install engine oil (2, Consumable Materials
Chart) before flight.
used to preserve the
engines.
The control lock holds the throttles closed and all
primary flight controls in the neutral position. The elevator and aileron controls are locked by a
locking pin
which slides into matching holes in the elevator shaft,
aileron torque tube, and control column
hanger.
A"other part of the lock slips over the throttles,
preventing them from opening while the elevator and aileron controls are locked. To insert the
locking pin,
place the elevator and aileron controls in an approxi-
mately
neutral
position.
A rudder control
locking pin, which joins and locks the
pilot’s rudder pedals, is attached to the control column
lock by a chain or cable. The pin is inserted in the
holes at the top of the pilot’s rudder pedal arms, where
it is retained by spring tension. Install the rudder lock
after first attaching the control column lock. Insert the
spring end of the rudder lock into the left-hand pilot’s
515
~eechcraft
BARON 55 AND 58
SHOP MANUAL
rudder pedal arm, neutralize the pedals, and insert the
opposite end of the locking pin in the other pedal arm
by compressing the spring.
To lessen the
possibility
of
taxiing
takeoff with the
or
control lock installed, remove the locking components
in the following order: rudder, elevator-aileron and
throttle.
(TC-1437
AFTER)
the neutral
controls
ing
the
center the bubble.
HOISTING
(Figure 2-1)
a.
The control lock holds the throttles closed, the elevator 11" down, and the aileron control wheel 12" right of
airplane may
Install
one
each forward
be hoisted
95-590017
wing
are
as
follows:
hoisting sling adapter
on
attach bolt.
NOTE
The throttle, elevator and aileron
locked by a lacking pin that is inserted
position.
between the throttle levers
hoisting the airplane with the
wings removed, install the 95-590017-1
sling adapters, and add a 95-590016-23
spacer between each sling adapter and
the spat carry-through fitb’ng. Install the
upper rear wing attach bolts. (See Figure 2-1.) The sling must be capable of
lifting 5,000 pounds.
When
the control column
through
matching holes in the
aileron torque tube. The portion of the lock that is
inserted between the throttle levers and through the
control column hangar prevents the throttles from
being opened.
hanger,
leveling is done by putting a bubble level on
baggage compartment fioorboard and deflattire or strut on the high side of the airplane to
rear
The
AND AFTER; TE-860 AND AFTER;
TH-223 AND
Lateral
the
the elevator shaft and
1
A rudder control
locking pin, which joins and locks the
pilot’s rudder pedals, is attached to the control column
lock by a chain or cable. The pin is inserted in the
holes at the top of the pilot’s rudder pedal arms, where
it is retained by spring tension,
The throttle control locks
are
to be installed in the fol-
b.
the
Attach the sling assembly (P/N 95-590016-1)
sling adapter.
c.
install the
the
nose
d.
Hoistthe
lowing sequence: Close the throttles, install the control locking pin between the throttles through the control column hanger, through the elevator control and
sling strap around the nose
landing gear (see Figure 2-1).
to
forward of
airplanesmoothly.
NOTE
Adjust the sling strap to keep the airplane in a level or slightly nose-down
the aileron torque tube. Route the cable and rudder
lock around the right side of the control column, posi-
attitude.
tion the rudder
pedals in the aft position and install the
rudder lock by inserting the spring end of the lock into
the left hand pilot’s rudder pedal arm. Neutralize the
pedals and insert the opposite end of the locking pin
in the other pedal arm by compressing the spring.
To lessen the
possibility
of
taxiing
or
takeoff with the
control lock installed, remove the locking components
in the following order: rudder, elevator-aileron and
throttle.
LEVELING
To level the
airplane longitudinally, attach a cord and
Phillips-head screw just aft of the
window on the U-l side of the airplane. Inflate or
plumb
rear
nose gear shock strut as necessary to
pass the cord through the center of a second Phillipshead screw directly below. Suspending the plumb bob
a can
515
(OPTIONAL
EQUIPMENT)
connecting an auxiliary power unit, turn off the
generator/alternator switches and any other electrically operated equipment except the battery switch.
The airplane has a negatively grounded auxiliary
power receptacle. If the auxiliary power unit does not
have a standard AN plug, check the polarity of the unit
and connect the positive lead to the battery positive
post and the negative lead to the battery negative post
and resume normal starting procedure.
Before
bob to the
deflate the
in
EXTERNAL POWER
of
light engine
oil will assist in
stabilizing
it,
NOTE
When using external electrical power,
the battery switch should be left on so
that the battery will absorb any transient
electrical
spikes.
2-25
’i~eechcraft
BARON 55 AND 58
SHOP MANUAL
/r
STRAP ADJUSTER
INSTALL 95-590017-1 ADAPTER
HERE WITH WING REMOVED.
INSTALL 95-590017 ADAPTER
HERE WITH WING INSTALLED.
95-590016-23 SPACER
WING ATTACH BOLT
95-590017 ADAPTER
0)
I
SPAR CARRY
THRU FITTING
SPAR CARRY
I
i I
o
THRU FITTING
WING SPAR FITTING
95-590017-1 ADAPTER
WING ATTACH BOLT
VIEW B
VIEW A
Figure
2-2F
24.
Hoisting
the
Airplane
E15
BARON 55 AND 58
SHOP MANUAL
has been started and the auxiliary
power disconnected, the electrical switches may be
turned on and normal procedures resumed. Recharging the battery without removing it from the airplane
After the
airplane
accomplished by connecting a known negatively ground auxiliary power unit to the airplane external power receptacle and turning the battery master
may be
switch ON. In
case
of
an
extremely
weak battery,
removing and recharging may be necessary since the
battery may not have sufficient capacity to close the
battery solenoid. It is essential that you make certain
that the power unit is
negatively grounded.
NOTE
a.
After each 100 hours of
days,
whichever
occurs
operation
or
every 30
first, check the electrolyte
level and clean the battery and filler vent
plugs.
Any time the battery is subjected to more than 32
as long as two minutes, the battery must be
cori~pletely serviced. Clean the battery, charge it, and
adjust the electrolyte level.
b.
volts for
Periodically check that the cell vents are clean
and open. Plugged vents may cause excess internal
c.
cell pressure and cause leaks.
Never remove a cell from the battery case unless
a replacement is immediately available; otherwise, the
remaining cells may swell, making replacement of the
d.
On airplanes TC-1011 and after; and
TE-197 and after, a protection feature is
incorporated into the external power circult to protect against a ground power
unit with reversed polarity.
removed cell difficult. Loosen the vent before cell
replacement to eliminate the possibility of’cells swell-
ing
e.
from internal gas pressure.
Check the torque of the terminal screws securing
connecting the cells together. This tor-
the cross-links
The
to
batte~y may be damaged if exposed
voltages higher than
30 volts,
SERVICING
Proper and periodic servicing of the airplane will prevent considerable wear and greatly lengthen the service life of parts and systems involved. For points of
lubrication and the correct interval and materials, refer
to the lubrication and servicing charts in this section.
BA TTERY
the access door
on
the
baggage
anything but distilled
NICKEL-CADMIUM BATTERIES
of battery servicing precautions and
checks is meant to be a guide. For specific details and
a complete procedure, see Section 13 of this manual.
515
damaged rubber parts.
and water only.
Do not use
a
solvent;
use
soap
Do not add electrolyte just because the level in
battery is low. If electrolyte is added instead of
distilled water each time the battery is low, the high
concentration of electrolyte may cause dissolution of
the
affected cells.
water to the lead acid
Do not overfill. When the battery cells
are overfilled, water and acid may spill
on the lower portion of the fuselage.
following list
When there is any indication of oil in the battery,
remove all cells from the case and check all rubber
parts for deterioration. Remove the oil and replace all
g.
plates under high temperature conditions. This is
indicated by the presence of black particles in the
battery. The water level in the BEECHCRAFT or Gill
battery should be maintained at 1/2 inch above the
separators.
NOTE
The
Check that
the
LEAD ACID BATTERIES
Never add
no carbon deposit has built up on the
them and the battery case. If
between
cross-links or
are
such deposits
present, clean the affected area as
indicated under Cleaning and Inspection, Section 13.
f.
h.
The battery is located beneath the baggage compartment floor on the right-hand side and is accessible for
servicing by opening
compartment floor,
to 5
.)sdnuoinch-pounds
p-to(4oi
que should be from 48 to 60
CAUTION
i.
Keep nickel-cadmium and lead-acid batteries
stored separately to prevent mutual contamination.
Unless kept in closed storage containers, nickelcadmium electrolyte (potassium hydroxide) will absorb
carbon dioxide from the air to render it ineffeo
enough
tive.
TIRES
The main wheel tires are 6-ply or 8-ply 6.50 X 8 tires
and the nose wheel tire is a 6-ply 5.00 X 5 tire. Maintaining proper tire inflation will minimize tread wear
and in preventing tire rupture caused from running
23
~eechcraft
BARON 55 AND 58
SHOP MANUAL
sharp stones and ruts. When inflating tires, visually inspect them for cracks and breaks. For correct
same
inflation
as
over
see
General Information in Section 1.
In service, tire carcasses grow slightly due to shock
landing. Normally, this growth is balanced by
loads in
tread
wear so
there is
no
and
procedure
is used for
servicing both
gear shock struts. To service
follows:
nose
a.
core
Remove the air valve cap and
to release the air pressure.
a
the main
strut
depress
proceed
the valve
increase in tire diameter.
Corporation cannot recommend the
recapped tires. The tires may pass the retraction test when first installed; however, recapped tires
have a tendency to swell after use and may cause
malfunction of the retract system or damage the landing gear doors.
Beech Aircraft
use
WARNING
of
Do not unscrew the air valve assemuntil the air pressure has been
bly
released or It may be blown off with
considerable force, causing In/ury or
property damage.
CAUTION
With the
b.
Because of
possible damage
to the
retract system or landing gear doors,
tires that measure more than 62.33
inches in circumference or 19.85 inches
in diameter should not be used.
Oil and other
hydrocarbons spilled
on
the tires not
weaken the rubber but may cause them to swell.
Avoid spilling oil, fuel or solvent on the tires and clean
only
off any accidental
spillage
as soon as
possible.
NOTE
While Seech Aircraft Corporation cannot
recommend the use of recapped tires,
tires retreaded by an FAA approved
repair station with a specialized service
limited rating for TSO-C62c may be
used.
weight of the airplane on the gear, loosen
assembly slowly to ensure that all air has
escaped, then remove the air valve assembly.
the air valve
With the shock strut
fully deflated, jack the strut
fully compressed, block it there and
fill to the level of the air valve assembly hole with
hydraulic fluid (13, Consumable Materials Chart).
c.
barrel 1/4-inch off
d.
Jack the main strut
the
oil to drain away, then install the air valve
assembly, depress the valve core
and lower the jack, releasing the excess air and oil.
On the nose strut, merely remove the block and allow
excess
assembly.
Rocking the airplane gently to prevent possible
binding of the piston in the barrel, inflate the nose gear
strut and main gear strut until they reach the dimensions which are specified in General Information, Section 1 (airplane resting on the ground).
e.
NOTE
The fluid reservoir, accessible through the forward
baggage compartment, should be checked regularly
a
It is recommended that the nose and
main strut inflation dimension and recommended tire pressure be adhered to.
Properly inflated tires and shock struts
reduce the possibility of ground damage
visible fluid level maintained
all times
Materials
on the dipstick at
by adding hydraulic fluid (13, Consumable
Chart).
occurring
LAND/NG GEAR
The
landing gear
additional 2 inches, then
air valve
BRAKES
and
an
replace the
to
propellers; however, exertaxiing over rough
cise caution when
retract mechanism is
complex system with very small clearances between working
parts. Adjustments should be made only at a BEECHCRAFT Authorized Service Station. Any malfunction
should be corrected by an Authorized Service Station.
surfaces.
a
f.
The shock strut
material
pistons must be clean. Remove
by wiping the strut with a cloth con-
foreign
taining hydraulic Ruid.
SHIMMY DAMPER
SHOCK STRUTS
The shock struts
are
To check the fluid level in the
filled with
compressed
air and
hydraulic fluid (13, Consumable Materials Chart). The
2-4
shimmy damper, insert
approximately 1/16-inch diameter through
the hole in the disc at the end of the piston rod until it
a
wire of
515
~eechcraft
BARON 55 AND 58
SHOP MANUAL
touches the bottom of the hole in the floating piston.
Mark the wire, remove and measure the depth of
insertion.
Inserting
rather than
piston,
piston,
will
give
b.
Every
the wire in the hole of the
letting
it hit
floating
against the face of the
Place the
1.
retract the
accurate check.
a more
and the center
To determine if the wire is inserted in the
hole of the floating piston, insert the wire
several times, noting each insertion
3.
uplock
rollers with sol-
follows:
airplane
on
jacks
and
partially
gear.
attaching
hinge point
Remove the
the
uplock
leg.
roller
of the "V" brace
uplock roller bearing
from the
bolt.
Hold
finger over one end of the center bearuplock roller and place the fitting of the
ing
grease gun against the opposite side of the bearing,
then pump grease into the bearing inner race. This will
force grease into the bearing cavity through the hole in
the inner race. Completely fill the bearing with grease
(11, Consumable Materials Chart).
4.
When the wire is correctly
inserted the length will be approximately
1/4 inch greater.
depth.
race
When the
shimmy damper is full, the inserted depth is
2-3/16 inches. The empty reading is 3-1/16 inches. To
hydraulic fluid (13, Consumable Materials Chart),
the shimmy damper and proceed as follows:
add
landing
as
Remove the bolt
2.
NOTE
100 hours clean the
vent and lubricate
a
of the
remove
a.
Remove the cotter
the
piston
washer and
pin,
spring
from
rod.
Remove the internal snap ring, scraper ring and
the end seal from the aft end of the barrel. (Opposite
end.)
Insert
c.
a
and
remove
ing
the
6/32-threaded rod into the floating piston
the
O-ring
Push the
barrel with
when
piston, using
extreme
seal of the
floating piston past
drilled holes in the
d.
care
mov-
hydraulic
TE-847 AND AFTER; TH- 1 75 AND AFTER,
AND PRIOR AIRPLANES IN COMPLIANCE
fluid
actuate the
Refill the
scraper
THE LANDING GEAR in Section 5 of this manual.
(13,
Consumable Materials
WITH S.1. 0448-21
Slowly
ring
displaced
piston rod, allowing
fluid and
and internal snap
g.
Fill the
h.
Reinstall the
piston
the fluid to
replace
ring.
pis-
the end seal,
rod with fluid.
uplock roller bearings should be lubricated with
grease (11, Consumable Materials Chart) every 100
hours or any time that while cleaning the wheel well,
the bearings are subjected to degreasing with solvent
under pressure. The uplock bearing is lubricated by
means of a grease fitting installed in the uplock bearing bolt.
floating piston, spring, washer and
pin. Spread the cotter pin to allow clearance for
the measuring wire.
NOTE
The grease fitting on the drag leg,
directly above the uplock roller does not
supply lubricant for the uplock roller
LUBRICATION OF LANDING GEAR
UPLOCK ROLLERS (PRIOR TO TC-1403,
bearing.
TE-847AND TH-175, UNLESS MODIFIED
IN COMPLIANCE WITH S.I. 0448-211)
Lubricate the
uplock
roller
bearings
HEATER FUEL PUMP
with SAE 20
SAE 10W30 oil every 50 hours. Every 100 hours
pack the bearings with grease (11, Consumable Mate-
or
rials
Chart)
degreasing.
515
or
any time the
bearings
are
subjected
1)
The
cotter
a.
clearance is not correct, the
indicated under RIGGING
as
to the clevis end and fill the
flow into the clevis-end chamber, then return the
ton to the clevis end of the barrel.
f.
clearance of .010 to .020 inch between the roller
uplock block. If this
uplock must be adjusted
and
LUBRICATION OF THE LANDING GEAR
UPLOCK ROLLERS (TC-1403 AND AF~ER;
piston rod.
piston rod
mum
attaching the uplock roller at
hinge point of the "V" brace drag leg.
uplock roller for free movement and a maxi-
the
Chart).
e.
Reinstall the bolt
Check the
b.
the clevis
5.
the center
to
After every 100 hours of airplane operation, remove
the heater fuel pump strainer by turning the base of
the pump counterclockwise. Wash the strainer in
clean PD680 solvent (15, Consumable Materials
Chart)
and blow
dry with compressed
air.
2-5
aeechcraft
BARON 55 AND 58
SHOP IVIANUAL
HEATER FUEL FILTER
provided
edge fuel
with 1 drain for the inboard wing leading
cell sump, fuel strainer and the wing fuel cell
sump in the box section of the wing.
NOTE
Airplane
serials TO-1406 and after;
TE-847 and after; and TH-176 and after,
do not have the heater fuel filter
installed,
Airplane serials TH-669 and after, equipped with wet
wing tips, are provided with the same 6 snap-type
drains (3 drains per wing) used on airplane serials
TH-1 and after, in addition to 1
each wet wing tip.
A fuel filter is installed in the nose wheel well next to
the heater fuel pump and filters foreign matter from
In
flush-type
drain for
the fuel. The strainer is equipped with a snap-type
drain and should be drained daily during cold weather
to remove accumulated moisture which, if allowed to
freeze, could cause heater malfunction.
injection-type system, most fuel malfunctions
be attributed to contaminated fuel; therefore, the
wheel-well-mounted strainers, finger strainers and
sump strainers should be inspected and cleaned regularly. The frequency of inspection and cleaning will
FUEL SYSTEM
depend upon the service conditions,
equipment, cleanliness and local sand
an
can
fuel
handling
and dust
con-
ditions.
NOTE
When
noule,
inserting
or
removing the
If
Goodyear fuel cells, manufactured
(Construction No. ETC-39
BTC-54A and ETC-67) are installed, no
preservation procedures are necessary
fuel
after 1961
extreme
care to prevent the
fuel hose from rubbing agains the deicer
boot. Also, do not allow fuel to contact
the deicer boot.
use
Service all fuel systems with aviation
(blue) preferred,
or
100
gasoline
when the cell is to be empty for an
indefinite period of time. The fuel cells
should not be open to the atmosphere
except for the normal
100LL
(green).
Airplane
serials TO-i through TC-1607; TE-1 through
TE-942 except TE-938, are equipped with a total of 8
snap-type drains (4 drains per wing). One drain in
each wing is provided for the inboard wing leading
edge
walls must be coated with
light engine oil.
more
Airplane
and
Airplane
serials TC-1970, TC-2003 and after;
TE-1081, TE-1084 and after, are equipped with a total
of 6 snap-type drains (3 drains per wing). Each wing
is provided with 1 drain for the inboard wing leading
edge
fuel cell sump, fuel strainer and the fuel cell
sump in the box section of the wing.
Airplane
serials TH-1 and after are equipped with a
total of 6 snap-type drains (3 per wing). Each wing is
2-6
thin coat of
a
MAIN FUEL STRAINER SCREENS
fuel cell sump, fuel strainer drain, auxiliary fuel
cell sump and the fuel system low point in each side
of cabin fuselage bottom,
serials TC-1608 through TC-2002, except
TC-1970; TE-938 and TE-943 through TE-1083,
except TE-1081, are equipped with a total of 8 snaptype drains (4 drains per wing). One drain in each
wing is provided for the inboard wing leading edge fuel
cell sump, fuel strainer, box section wing fuel cell
sump, and the fuel system low point tin each wing).
vent lines in the
airplane. Goodyear fuel cells manufactured prior to 1961 and Uniroyal fuel
cells must be filled every ten days or the
Inspect
and clean the screens each 100 hours
or
frequently depending on the service conditions
when operating in localities where there is an
excessive amount of dust
or
sand in the air.
INSPECTION PROCEDURE
a.
Place the fuel selector to the OFF
b.
Drain the fuel strainers.
c.
Remove the
safety wire
d´•
Remove the
screen
e.
Clean the
screen
and
position.
and strainer bolt.
inspect
and blow
dry
for contaminants.
with
f.
Replace
the
g.
Tighten
the strainer bolt and install
h´•
Place the fuel selector to the ON
i.
gasket and install the
dry air.
screen.
safety
wire.
position.
Place the mixture control to the OFF
position.
515
~i)eechcradt
BARON 55 AND 58
SHOP MANUAL
I
j.
Turn the boost pump ON to pressurize the fuel
at the fuel strainer.
WARNING
system. Check for leaks
k.
Turn the boost pump OFF.
Due to air
SERVICING AIR CONDITIONING SYSTEM
(TE- I 1 19 TE- 1 125 AND AFTER; TH-873,
TH-895 AND
AFTER)
NOTE
original air-conditioning installation
prior to TH-1745 used R-12
refrigerant while serials TH-1745 and
after use R-134a refrigerant.
The
for serials
will
Servicing the air conditioning system consist of periodically checking the refrigerant level and changing
the system air filters (both forward and aft evaporator
filters). Recharge the system whenever the refrigerant
level is low, air has entered the system
or
components
ensure a
are
on
removed,
good seal.
CHARGING THE AIR CONDITIONING SYSTEM
ARNING
recharged
worn
when
when:
refrigerant level is insufficient or the refrigerthrough the sight glass in the receivercontains
bubbles or appears milky.
dryer
b.
Leaks have been detected in system.
c.
Air has entered the system.
Components carrying refrigerant
replaced.
d.
nections
815
ambient temperature of 75"F
as
ant observed
recycle/recovery servicing unit
located under the copilot’s seat.
Hook the
R- 134a
or
above.
observed
sdisappear
elbub.tnaregthrough
irfer
The
a.
an
a
or
then add
servicing the lines; refrigerant, comIng In contact with the eyes, can
cause the loss of sight
The system should be
refrigerant.
If it is necessary to add refrigerant to a partially
charged system, add refrigerant slowly until the
I
A face shield should be
the
completely purged system with 3 pounds of
refrigerant (34 or 63, Consumable
Materials Chart) On airplanes TH-1 thru TH-1744 use
R-12 refrigerant. On airplanes TH-1745 and after use
R-134a refrigerant. When charging the system,
observe the sight glass for bubbles or a milky appearance caused by an insufficient refrigerant level. On a
fully charged system the sight glass should be clear in
R-12
the air condinew Seco
7A washers of the proper size should be
used when reinstalling the lines to
If the flared freon lines
salvage
possible damage to the compresser, refrigerant is to be added to the
system in the vapor form to prevent liquid slugging. The compressor does not
have to be run during the charging cycle.
Charge
tioning system
regulations
To prevent
replaced. Refrigerant leaks
carrying refrigerant
with a flameless leak
be
detected
by
inspection
may
NOTE
control
NOTE
are
detector.
quality
being enacted In the United States,
R-12and R-134a refrigerant cannot be
vented into the atmosphere. When
performing maintenance on the vapor
cycle system where refrigerant R-12
or R-I34a can escape from the system, evacuate the system with a
recovery or recycle servicing unit that
an
additional two
ounces
the
sight glass,
of
MPANSION VALVES
Even though the expansion valves are of the
adjustible type, it is impossible to properly adjust them
on the airplane. The expansion valves are adjusted at
the factory to 38~ .5 psi, but without proper equipment, a satisfactory adjustment can not be achieved.
If the valves are not operating properly, replace the
valves with
new ones.
REPLENISHING AIR CONDITIONING SYSTEM
LUBRICATION
Under normal
have been
to the con-
operating
conditions the oil
charge
in
the compressor should not require periodic checking.
Unless the system has suffered a catastrophic failure
or severely leaking compressor
seal the system should not need the oil checked.
such
as a
broken line
2-6A
’j~eechcraft
BARON 55 AND 58
SNOP MANUAL
NOTE
i.
Charge the air conditioning system as noted in
CHARGING THE AIR CONDITIONING SYSTEM.
If the system is opened after the initial
charging, measure any oil lost in opening the system and add to the system
only an amount equal to the loss,
I
Check the area around the filler plug for leaks. If
leaks exist, do not overtighten the filler plug. Remove
the plug as noted in step e and install a new O-ring
j.
To maintain four ounces of oil in the compressor, the
air conditioning system requires 11 to 12 ounces of
500 viscosity oil (35, Consumable Materials Chart) on
TH-1 thru TH-1744, or 13 ounces of oil (67,
Consumable Materials Chart) on airplanes TH-1745
and after. Satisfactory operation depends on sufficient
airplanes
after depressurizing the system with a recycleing service unit. Secure the plug and recharge the system as
noted in steps h and i. In order to accur~tely determine the oil level of the air conditioning system, the
lubrication, but
system should be operated for several minutes and
the compressor removed, immediately after shutdown,
as noted in COMPRESSOR REMOVAL IN Section
10, Drain the oil from the compressor into a measuring cup. If the total amount of oil drained from the
Check the compressor oil level
compressor measures 3-4 ounces, the system is fully
If the amount is less than three ounces, add
a necessary amount of oil to bring the total level to 4
OU"CeS and pour this amount back into the
compres-
too much oil will decrease cooling effiThe
air
conditioner
ciency.
compressor oil level should
be checked by a qualified air conditioner service man
if the refrigerant charge is lost,
as
follows:
Fabricate
a.
angle
so
a dip stick by bending a wire to a 90"
that 1-1/2 inches of the wire will insert into
the compressor.
b.
Paint the
dipstick with a flat black paint.
paint to dry.
Allow sufL
ficient time for the
Start the
c.
Pilot’s
engine
in accordance with the
applicable
Operating
Handbook and run the air conditioning system for 15 minutes with the engine running at
low rpm to allow the oil to accumulate in the compressor. Observe the engine operating limitations as noted
in the
applicable Plot’s Operating Handbook. Shut
engine in accordance with the applicable
charged.
Reinstall the compressor as noted in COMPRESSOR INSTALLATION in Section 10.
SO’’
ENGINE INDUCTION MANIFOLD DRAIN
Induction manifold drains permit excess fuel to drain
overboard by means of a ball-check valve or a drilled
orifice attached to a boss fitting at each rear manifold
and at the transfer tube at the forward lower engine
section.
Inspected the valves at each 100 hours of
engine operation to prevent malfunction and possible
contamination.
down the
Pilot’s
Operating
Handbook.
d.
Relieve the system pressure
recycle servicing unit.
Remove the oil filler
e.
f.
Insert the
by evacuating
with a
the oil filler port.
Slowly
dipstick
will
Withdraw the
dipstick; oil should appear on the
inch below the oil filler port. Add oil as
necessary to maintain this oil level.
dipstick 5/8
NOTE
Make sure that the O-ring is not twisted
and that dirt and or foreign particles are
not on the seat of the plug. The piug
should be snug Do not overtighten the
plug.
h.
Install and
plug to
O-ring.
2-68
6 to 9
new airplane is delivered with Rustband oil (MI1C-6529, Type II) in the engine. It is recommended that
corrosion-preventive
engine operation,
hours of
rotate the compressor clutch untill the
insert to the bottom of the compressor.
g.
The
this
plug.
dipstick through
BREAK-IN ENGINE OIL
oil be
must never exceed 6 months of
oil
change.
Oil
as
changed
and the
use
at 20-25
of Rustband oil
operation before
an
If the Rustband oil is not removed at the
varnish may form in the engine. Oil contime,
proper
f0’ming to MlL-L-6082 may be added to the Rustband
and
necessary. After removing the Rustband oil, refill
MlL-L-6082 mineral oil until oil consumption
use
has stabilized. After oil consumption has stabilized, an
ashless dispersant oil, complying with Continental
Motors’ Specification MHS-248 and MIL-L-22851,
must be used. For several suitable engines oils, see
the Consumable Materials Chart, Item 2.
NOTE
A 75% power
secure
the oil filler
foot-pounds.
If the
plug. Torque the
plug leaks replace the
setting is recommended
during the break-in period. Avoid overcooling caused by long power-off and/or
rapid descent.
E~5
aeedmcradt
BARON 55 AND 58
SHOP MANUAL
ine
011 SYSTEM
operation. Replace
with
oil which is used until oil
NOTE
new
mineral
consumption
stabilizes.
engine break-in period and at each
change thereafter, use only detergent
oil meeting Teledyne Continental Motors
Specification MHS-24B for all Continental engines. The break-in oil in the engine when the airplane is delivered from
the factory is a Rustband oil (MIL-C6529, Type II) and should be changed
After
oil
after 20 to 25 hours
515
or
6 months of eng-
2-6C
BEECHCRA~T
BARON55 AND 58
SHOP MANUAL
The
engines
equipped with a wet sump, pressure type, oil
system. Each engine sump has a capacity of 12 quarts.
Servicing the oil system is provided through access doors in
the engine cowling. A calibrated dip stick adjacent to the
are
filler cap on TC serials and attached to the filler cap on TE
and TH serials indicates the oil level. Due to the canted
reinstalling. Upon reinstallation the oil
filter screen plug should be torqued to 500 to 570
inch-pounds. If slush deposits are heavy, subsequent oil
changes should be made at more frequent intervals.
and
damage prior
to
below
grades listed
The oil
are
general
recommendations
position of the engines, the dip sticks are calibrated for either
right or left engines and are not interchangeable.
only, and will vary with individual circumstances. Any
detergent aviation grade engine oil which meets Continental
Motors Corporation Specifications MHS-3-48 is acceptable
Under normal
for
operating conditions, the recommended
operating hours between oil changes on ail TC
number of
serials is 25 hours. A
change interval is
provided the oil tilter
element is changed at each oil change. When operating under
adverse weather conditions or continuous high power
settings, the oil should be changed more frequently. Torque
disposable type oil filters 216 240 inch-pounds. Torque
100 hour oil
recommended for all TE and TH serials
cartridge
Engines
type oil filters 180
manufactured after
TH serials,
use
216
RECOMMENDED OIL GRADES FOR ENGINES
Oil Inlet
Ambient Air
Recommended
Temp.
Temperature
Viscosity
Desired Max.
Above 40"F
SAE-50
170"F 225"F
Below 40"F
SAE-30
inch-pounds.
April, 1975,
used
oil filter which has
an
use.
a
on
the TE and
by-pass
valve
641584)
are a
gold
an
15W50
All temperatures
color.
or
10W30
oil filter adapter with the by-pass
designed
valve eliminated. The later oil Alters (P/N 631383 and P/N
into it and
20W50
CAUTION
The earlier oil tilters
637583)
are a
During cold weather the
pre- flight inspection to be
(P/N 632399
and PIN
ice.
black color and MUST NOT be
engines manufactured after April, 1975,
gold oil filter has an adapter
without the by-pass valve.
used
oil sumps should be checked at
that they are not blocked with
sure
on
since the later
Also, since there may be
weather
starting,
with
an
more
cylinder
blow- by
attendant increase in oil
during cold
sludge, che
oil pressure screen should be checked more frequently and if
indicated, the oil drain intervals should be shortened.
OXYGEN SYSTEM
(OPTIONAL)
However, the gold oil filter (PIN 641583 and PIN 641584)
can
be used
on
either oil filter
adapters
without any
WARNING
modifications.
The oil may be drained by opening the drain valve on the
bottom inboard side of the oil sump, the low spot of the
system. Before draining the oil, the engines should be
warmed up to operating temperature to assure complete
of the oil. Moisture that may have condensed and
Avoid making sparks and keep all burning
cigarettes or fire away from the vicinity of the
airplane. Make sure the oxygen shut-off valve
on the console is in the closed position. Inspect
the filler connection for cleanliness before
attaching if to the filler valve. Make sure that
draining
settled in the oil sump should be drained by occasionally
opening the oil drain valve and allowing a small amount of oil
your hands, tools, and
particularly of grease
escape. This is particularly important in winter, when the
moisture will collect rapidly and may freeze.
to
and
pull
Wash the screen in solvent
Materials Chart) and dry with
the screen for physical deterioration
compressed
Eil
oil,
are
for
dean,
these
contact with
slowly during filling.
out the screen.
(Item 15, Consumable
air.
or
ignite upon
pure
oxygen under pressure. As a further precaution
against fire, open and´• close ail oxygen valves
contaminants will
The oil pressure screen (installed in TC serials only) should
be cleaned at each periodic oil change. To clean the oil
pressure screen, remove the hex head plug directly below the
starter
clothing
Inspect
recharging the oxygen system remove the
the filler valve and attach the hose from
from
cap
When
protective
an
oxygen
2-7
BEECHCRAFT
BARON~ 55 AND 58´•
SHOP MANUAL
filler valve. (The oxygen cylinder prior
to serial TC-j02 is located behind the cabin aft bulkhead. On
serials TC-S02 and after, and TE- L and after, the cylinder
and filler valve
of the
nose
are
Located in the forward
absolutely certain
Make
secure.
utility compartment
section).
Never operate the "Delcotron" on open circuit.
all connections in the circuit are
d.
recharging cart to the
Do not short
e.
on
the "Delcotron’’
Do not attempt
f.
To prevent overheating, fill the oxygen system slowly by
adjusting the recharging rate with the pressure regulating
valve on the cart. The oxygen cylinder should be filled to a
C
50 psi at a temperature of 700F. This
pressure of 1850
increased
be
an additional 3.5 psi for each
may
pressure
degree of increase in temperature; similarly, for each degree
in temperature, reduce the pressure for the cylinder
by 3.5 psi. When it becomes necessary to disconnect a fitting
refer to the table of thread Lubricants for correct thread
lubricant before connecting the fitting back into the system.
of
drop
to
polarize
any of the terminals
the ’’Delcotron."
testing, brush replacement and
Delco-Remy Service Bulletins IG-262
For additional overhaul,
lubrication, refer
to
and IR-273.
LIGHTWEIGHT SURFACE DEICER SYSTEM
(RESERVOIR-TYFE)
Pull the air
a.
valve is full open.
Remove the
b.
MAGNETOS
ground
regulator.
across or
or
supply
valve control
yellow
cap
on
out so
that the
the reservoir filler
valve.
Ordinarily, the magnetos will require only occasional
adjustment, lubrication and breaker point replacement.
Attach the filler hose
c.
nut on the
valve
i.
The internal automatic grounding devices used
on the original S series magnetos have proved
unreliable in service and current production
magnetos do not have this feature. To be safe,
treat all S
series, S200 series, and S 1200 series
magnetos
as
hot whenever the
the wire to the
impractical,
the
engine
ground
2.
of the magneto
plug leads.
rear
spark
or
case.
If
observe these
damage
to
the electrical
serious
or
Charge the reservoir to a pressure of 2800 It 200
compressed air or nitrogen.
dry
psi
e.
Tighten the hex nut, remove the fiiler hose, replace
the safety cap, and close the air supply valve.
d.
with
~ounding
plate on
PF~OPELLER ANTI-ICER SYSTEM
(ALCOHOL)
The anti- icer tank is located beneath the left tloorboard of the
forward utility comparaent and has a capacity of 3 U.S.
are
designed
for
use
on only one polarity system, therefore, the following
precautions must be observed when working on the charging
to
Never service the system with oxygen
disconnect all the
regulator
circuit. Failure
Connect the filler hose to the filler valve
releasing the filler valve locking device.
lead is
DELCOTRON ALTERNATOR
The Delcotron alternator and
the hex
corrosive gases.
the cable outlet
remove
nun
L/4 nlrn´•
before
disconnected. To ground the magneto, connect a
wire to the switchlead at the filter capacitor and
is
the valve and
WARNING
CAUTlON
~Iound
to
assembly counterclockwise
precautions
equipment.
will result in
The tank filler cap may be reached by removing an
door in the floor of the utiliry compamnent. Cneck the
tank t’luid level before each cold weather flight and refill with
anti-icer fluid (Item 30, Consumable Materials Chart), if
drained and flushed twice a
necessary. The tank should be
gallons.
access
year.
installing a battery, always make absolutely
sure the ground polarity of the battery and the ground polarity
a.
When
of the "Delcoaon"
are
the
connecting a booster battery, make certain
to connect the negative battery terminals together and the
positive battery terminals together.
When connecting a charger to the battery, connect
c.
the charger positive lead to the battery positive terminal and
the charger negative lead to the battery negative terminal.
b.
2-8
When
NOTE
same.
The anti-icer tank should be flushed
only
with
anti-icer fluid (Item 30, Consumable Materials
Chart). The use of other types of fluids may
cause chemical reaction that will corrode
aluminum. This will create a gummy residue in
the system and make the system inoperative.
Ell
BBEOHORAFT
BARON 55 AND 58
SHOP MANUAL
Install the instrument in the instrument panel if
secure in place with the attaching screws.
b.
INSTRUMENT ACCESS
removed and
To
gain
access co´•
the
instruments
flight andlor engine
BEECHCRAFT Baron, proceed
as
on
the
glare shield,
a.
Remove the
b.
Disconnect the
plumbing
and hoses
the base of
at
the electrical
flight instruments and unplug
engine instntments.
the
plugs
on
wedge Light (TE-768 and
and
TH-1
holding
after)
after;
by
up and tilting the
instrument, then thru the instrument panel mounting
opening, remove the two screws that attach the light tray to
the instrument bezel. Separate the light tray from the
instrument and remove the instrument from the airplane.
Radio equipment located on the right hand side of
d.
the instrument panel may be removed as an assembly or as a
and remove
separate unit. To remove as an assembly, loosen
the bordering attach screws from the radio panel, pull straight
out and unplug the electrical plugs. To remove a single unit,
loosen the attach screw on the unit and pull the unit stnight
out,
flight instruments, engine instruments
equipment by reversing the above procedure.
Install the
e.
and radio
REPLL\CING THE GYRO INSTRUMENT AIR FILTERS
of the ,oyro instrument air filters may be
accomplished without removing the instrument from the
The frequency of cleaning or replacing the air filters
The
airplane.
will depend
be checked
When
should
upon service conditions; however, they
approximately every 100 hours of operation.
in localities where there is an excessive
operating
amount
of sand
or
dust in the air,
additional
provides
light
mounted
trav
holds
the top side of the bezel of each instrument
wired in parallel. If the light bulbs are damaged
the light tray with bulbs must be replaced.
two
buibs
burned
or
on
out
subjected
when
or
to
(tobacco), the filter should be
inspected and replaced at more frequent intervals if
conditions, it may be
necessary. Under extremely dusty
filter reduces
necessary to inspect the filter daily. ,4 cloPoed
causing
the
improper yyro
rotor,
air tlow and slows up
continuous cabin smoke
indication due
to a
loss of
inertia.
gyroscopic
the instrument.
replace the filter assembly on
body cover by taking
out
remove
the
the four tlllister-head
out the snap ring which holds the filter
filter, and replace it with a.new one.
the
in place, remove
the air filter body cover and gasket, securing them
machine
of the instruments
illumination across each instrument. A
replacement
air filter
INSTRUMENT WEDGE LIGHTING
(TE-768 and after, TH-1 and after)
lighting
I
VACUUM SYSTEM
To
Internal
place.
the
Remove the instrument
c.
in
panel
Secure the instrument
c.
follows:
screws.
Lift
screws.
If the air filter
Replace
with the
filter may be removed
body
by lifting
is not used, the
ring past the four
cover
the snap
protective lugs.
LIGHT TRAY REMOVAL
CENTRAL AIR FILTER
a.
in
panel
to the
Remove the
place
screws
that
and tilt the instrument
secure
panel
the instrument
aft to
gain
(TC- 10 14
and after, TE-IOS and airer)
access
A central instrument air filter (two installed on airplanes
with dual instrumentation) is incorporated in the
the instruments from
Lines to
instrument
instruments.
equipped
plumbing
Instruments
panel may
to
the
located
at
the lower
be removed if necessary
light tray
at
be
edge of the
to gain access
or
replaced every
heavy
Locate the filter(s), mounted
a.
b.
screws
that attach the
light tray
to
control
panel
housing
LIGHT TRAY INSTALLL\TION
c.
the two
811
attaching
new
screws.
light tray and
secure
in
place
with
the base of the
wing
centrally behind
d.
reversing
the attach
nut
at
the base of the filter
by
clips.
Discard the old filter and install
the above
the
panel.
and remove the filter from the bracket.
Disconnect the hose at the top of the tilter
removing
Install the
at
Remove the
b.
the instrument bezel.
a.
during operation in dusty
Replacement is made as
500 hours (or less
smoke conditions).
follows:
the top of the instruments.
Remove the two
protect
dust and other foreign particles. This filter(s) is a sealed unit
mounted on a bracket behind the instrument panel and should
NOTE
a
new
filter
by
procedure.
2-9
BEECHCRAFT
BARON 55 AND 58
SHOP MANUAL
PNEUMATIC PRESSURE SYSTEM
(TE-~52 and after, TC-Z003
are located in, and may be serviced through,
door in the top inboard side of each nacellz.
accumulators
and after, TH- I and
after)
access
FILTER REPLACEMENT
I
SEATS
The
pneumatic system has four filters which need to be
replaced periodically. The inline Filters are located directly
down stream from the pressure regulators in each engine
compartment and should be replaced every 300 hours or
sooner depending on conditions. The intake tilters are
located on the forward side of each engine rear baftle. The
ROTON LOCKS
(Figure 2-2)
Usually,
grinding
as
Roton locks will need
and
in the lock
binding
follows should
the
sent
reclines
a
the
or
jerky, a little grease properly applied
improve the operation.
serials TE-937 and after, TC-7,003 and after, TH-373 and
after, and earlier airplanes which have complied with
Humble Oil Co., Houston,
BEECHCRAFT Service Instructions ~lo. 058 1 19J, the
intake filter (Figure 2-1A) should be replaced annually or
cause
Use only
a.
Enco ANDOK-B
Texas)
on
erease
the thread
(product
as
of
shown in
Figure’- 2, Too much grease or grease in the wrong place can
improper operation.
b.
Compress the spring guide and counter-balance
spring approximately one inch.
Remove the retaining ring.
c.
d.
Relax pressure on the spring guide and
counter-balance spring slowly until the spring is fully
every 300 to S00 hours of service time. This tilter element
must not be subjected to solvent and must be replaced if this
4lways reinstalI the filter cover with the opening
~ny time a pump is replaced the inline filter
be replaced.
occurs.
must
service. If there is
no
as
action becomes
return
foam type filter should be removed each 100 hours, washed
in solvent, and blown dry with low pressure shop air. On
facing
an
down.
extended,
Remove the lock from ~he fixture and
2.
rpring,ouide.
f.
Apply
counrer-
PROPELLER UNFfATHERING ACCUMULATORS
extended thrust
To insure proper operation, the accumulator should be
checked periodically for correct pressure. When checking the
air pressure, the propeller control should be in the low pitch
position
so
that all oil
can
be exhnusted
a
small
HYDROLOK
seat back adjusters need service they may be
P.L. Porter Co., 6355 DeSoto ,-\ve., Woodland
Hills, Calif. 91364.
If the
propeller accumulators
psi. When inflating the
dry air or nitrogen. The
hydrolok
to
FILTEII
MOUNT
r
ITOs
OI(Lll ´•IN 0.´•1´•-11
i
II
spring..lnd jpting
quantity of grease to the completely
from the
accumulator,
NVT,
the
See Finure ’--2.
screw.
returned
commercial
remove
guide tube.
Reassemble the lock.
g.
accumulator The pressure in the
should be maintained at LOO C 5
use
balance
r
nN~15.3a NUT
I
I
-iI:
ii
’I
i
I!
I
IOCK W/LS~ER
_...
NUT ~ND W*SH(R
716 W*SHII
lrD-190-19
Figure
2-10
L*N~70-3 W~SHER
2-1A. Air Filter
Replacement
Ell
BEEOHORAFT
BARON 55 AND 58
SHOF, MANUAL
INSTALLATION OF FLARED FITTINGS
LUBRICATION OF GASKETS AND SEALS
When installing flare fittings, make sure the male threads rue
properly lubricated. Torque the fittings in accordance with
the Flare Fitting Torque Chart in Section i. Do not
Gaskets and i’0"
over-torque.
EXTERIOR CLEANING
LUBRICATION OF THREADS
Prior to
(Figure 2-3)
certain that wheel brakes
ring seals requiring lubrication are
they are sealing.
cleaning
be
making
the exterior, install wheel covers,
jecurely; install plugs in,
are
covered; attach pitot
mask off, all other
or
covers
openings.
Be
mask off both static air buttons before
plumbing fittings on external lines, including their points of
attachment at the engine, the threads on the oil pressure
particularly careful to
washing or waxing.
transmitter and other component shall be lubricated with the
proper lubricant as specified in Table Of Thread Lubricants.
WNPAINTED SURFACES
All
to
lubricated with the fluid type which
When applying thread lubricants, the following rules should be
Use a’iBon-Ami’’ type mild abrasive for cleaning unpainted
clad aluminum and stainless steel surfaces and for removing
stains and embedded surface dirt. These cleaners, while they
observed.
a.
Clean threads before
b.
Use
c.
d.
applying
lubricant.
only thin coats of selected thread
Apply lubricant to male threads only,
On straight thread fittings, lubricate
lubricant.
the first 3
threads,
2.
threads.
f.
bright metal finish to the surface, remove any wax
that may be on the surface; rewaxing will be necessary. Use
cleaner sparingly, applying directly to the surface with a
restore a
clean
On
first
tapered thread fittings, do not lubricate
Apply lubricant to next i threads only,
Never allow lubricant to enter
fittings
1
damp
cloth. Rub
dirt with another clean
or
flare
briskly
so
the dirt and oxide film. Remove
clean
dry
cloth. Rub
that cleaner will penetrate
cleaner and dissolved
excess
damp cloth,
to
obtain
a
and
polish
smooth
surface with
polished
a
finish.
areas
Engine fittings should be lubricated only
transported in the line, i.e. engine oil, t‘uel. Air
g.
fluid
not
with the
lines
PAINTED SURFACES
are
lubricated.
removing dirt, grease and bug juice t‘rom
are easily obtainable, such as a cellulose
painted
mild
or
absolutely no synthetic detergents
soap
sponge,
can be used
naphtha, a few clean white rags, a chamois
and lots of cool water. When removing dust and dirt, use a
cellulose sponge rubbing in a circular motion and adding
water when needed. Dry with chamois to prevent water
The materials for
surface
the
RUBBER SEALS
Deterioration and/or
sticking of rubber seals around doors,
cowlings may be prevented by coating them
with Oakite 6 compound, (product of Oakite Products inc.,
19 Rector St., New York 6, New York). No special care is
required when applying the compound to keep it from
coming in contact with any painted surfaces. The compound
is non-injurious to paint and may be removed by employing
normal cleaning methods.
windows and
marks.
Oil and
crease can
naphtha.or removing
leading edges
and
rag dampened with
bugjuice which adhere to the
be removed with
dust and
nose,
use
a
a
mild soap solution and
a
RETAINING RING
FUUY EXTENDED
SPRING GUIDE
(APPAOX)- APPLY GREASE
(LIGHTLY HERE ONLY)
3/4"
ABSOLUTELY NO GREASE
IN THIS AREA
SPRING GUIDE TUBE
MAIN ASSY
COUNTERBALANCE
SPRING
Figure
511
2-2.
Servicing
8431e1
Roton Chair Lock
2-11
BEECt´•ICFIAR
BARON 55 AND 58
SHOP MANUAL
LUBRICATE
TAPERED
LUBRICATE
LUBRICATE
PIPE THREADS
DO NOT LUBRICATE
FEMALE THREADS
STRAIGHTTHREADS
NEVER ALLOW LUBRICANT
r0 CONTACT THIS SURFACE
Figure
cellulose sponge. Do nor
harsh soaps. Do not use
use
a
a
hard
synthetic
2-3, Lubrication ct Threads
detergent
scrubbing
or any
action with the
sponge. Flush the entire surface with water
traces of soap and dry with a chamois.
ao´•so4´•5
to remove
all
superficial
corrosion. Smooth etched and
Be sure ignition
a.
cleaning propellers.
b.
if a liquid Cleaner
ENGINE CLEANING
The engine may be cleaned with kerosene, Stoddard solvent,
or any standard solvent recommended for cleaning engines,
The cleaner may be sprayed or brushed on the engine. Wipe
the engine dry; compressed air may be used to remove
excessive oil.
picted
areas
by
buffing smooth with an aluminum polish. Take the following
precautionary measures while cleaning the propellers:
switches
are
;’OFF"
before
is used, avoid using excessive
because it may spatter or run down the blade and
the hub or engine accessories.
amounts
enter
c.
Check
area
around hub to be
sure
all
compound
is
removed,
LANDING GEAR AND TIRES
CLEANING THE ENGINE INDUCTION AIR FILTERS
Emulsion type cleaners
The induction air intake tilter, in the induction air box on TC
serials, and below the airscoop on TE and TH serials,
provides filtered air to the air metering section of the fuel
injection system. The filter should be removed and cleaned
every 50 hours (up to a maximum of 10 times) or more often
when operating in dusty conditions. See Donaldson
instruction Sheet No, Pl1-6704 or subsequent for cleaning
instructions. The filter should be replaced after 500 hours of
service or one year, whichever occurs first. If, after cleaning,
metal wires are showing or the filter shows other damage, it
should be replaced.
To
remove
the air filter for
the air filter access
the oil
access
cleaning
on
TC serials,
remove
plate
in the top of the engine cowling aft of
door. Then remove a second access plate on the
are
recommended for
gear. These solutions usually contain solvents which
are injurious to rubber if allowed to remain in contact for any
length of time. If these solvents come in contacr with tires as a
result of other
removed with
a
cleaning operations. the
thorough water rinse.
R/losr
compounds
used for
removing oil,
dirt tiom wheel wells and nacelles
These
Cover
PROPELLERS
CLEANING DEICER BOOTS
are
subject
to severe wear and
atmospheric
corrosion. Brush
2-12
area
with
a
phosphatizing agent
to remove
grease, and surface
emulsifying agents.
petroleum solvents,
openings and air scoops.
During cold weather (if water rinse is used) remove
evidence of water by blowing out with an air gun. Any
a.
any
propellers
are
compounds, when mixed with
emulsify the oil, grease, and dirt. The emulsion is then
removed by rinsing with water or by spraying with a
petroleum solvent. Take the following precautionary
measures while cleaning the wheels and nacelles:
air scoop on the upper engine cowling and lift out the filter,
Clean the filter as specified by the manufacturers instructions
on the filter.
conditions, check blades and dome for oxidation and
solvent should be
WHEEL WELL AND NACELLES
top of the air box and slide out the filter. To remove the Rlter
on TE and TH serials, remove the access plate on
top of the
Since
cleaning
landing
b.
water
that remains mav freeze and lock the controls.
The boots should be checked for
and
engine
oil after
servicing
the end of each flight, and any oil found should be
removed. This can be accomplished, preferably, by the use
at
511
8EECHCRAFT
BARON´• 55 AND 58
SHOP MANUAL
of
a neutral soap and water solution. If necessary, however,
the oil may be removed by wiping the boot surface lightly
with a rag moistened with toluol or uncontaminated unleaded
on
plastics
craze or
as
they
have
ii
tendency
to
soften and
scratch the surface.
aviation
be
gasoline. When ~asoline is used, the surface should
wiped dry immediatery without allowing the gasoline to
penetrate into the rubber. Also
avoid
scrubbing
remove
the thin
care
should be exercised
the surface of the boot
coating
as
this will tend to
of conductive cement,
NOTE
Since deicer boots
stock,
are
made of soft, flexible
be exercised
against dragging
gasoline hoses over them or resting ladders or
platforms against the boor’s surface.
care must
FINAL WAX APPLICATION
to
thorough waxing protects painted and unpainted metal
by preventing salt air, smoke, moisture and exhaust
gas attacks; it retards adherence of sticky nirt~orne dust and
minimizes corrosion. The frequency of rewaxing is
dependent upon frequency with which regular maintenance
cleaning is performed. Apply wax with a soft damp cloth.
Rub on surface with a light circular motion, covering an area
of approximately two square feet at a time. Polish with a
clean dry cloth.
A
surfaces
CAUTION
PLASTIC WINDOWS
delivery, painted surfaces should not
polished or waxed until the finish has cured
for at least 90 days. No hard rubbing, abrasive
At time of
Ordinary cleaning
of the
plastic windows in the pilot’s
compartment will cause severe damage to the surfaces and
will result in limited vision or costly replacements. To
prevent scratching, or distortion of the plastic windows,
special care must be taken when cleaning them. Flush the
surface with clean water, using the bare hand to dislodge any
dirr or abrasives. This will prevent the possibility of
scratching the surface during the washing procedure. ~Xlash
thoroughly with a mild soap solution, taking care that the
water is free from all possible abrasives. A soft cloth,
sponge, or chamois may be used to apply the soap solution.
Light films of oil or grease may be removed with trisodium
phosphate completely dissolved in water. Stubborn oil or
grease on the surface may be removed by rubbing lightly with
a clean cloth dampened with hexane, aliphatic, naphtha, or
methanol. Flush with clean water and then dry the surface
with a clean damp cfiamois. After the surface is dry,
continuous rubbing should be avoided as it is likely to cause
scratches, also it builds up a static charge which attracts dust
particles to the surface. If the surface should become
charged, patting or gently blotting with a clean damp
c17amois will remove the dust and the charge.
When the
airplane is equipped with windshield wipers use
only Curries-Wright CW-100 cleaner and dust repellent to
clean the windshield. Cleaner and repellant may be obtained
from Curtiss-Wright. ,Marquette Division, Cleveland, Ohio.
For additional information concerning windshield cleaning,
refer
to
be
cleaners
curing
or wax
seals detrimental to the proper
of the finish should be used.
INTERIOR CLEANING
the seats, rug, upholstery panels and head lining
should be vacuum-cleaned to remove as much surface dust as
Frequently
possible.
Experience has shown that commercial foam-type cleaners or
’‘shampoos" can be used to condition the surface of rugs,
carpets and upholstered materials. The upholstery is first
vacuum-cleaned, stains removed, then
.eleaner is
prepared by mixing
a
small
water, and beating the mixture until
Apply
a
the foam
brush, then
uniformly
remove
over
a
a
solution of the
amount
heavy
in
a
bucket of
foam is formed.
the surface to be cleaned with
the suds with
a vacuum
cleaner,
or
by
cloth. Since there is very little
moisture in this foam, wetting of the fabric or retention of
wiping
off with
a
brush
or
moisture in the warp does not occur. Unlacquered metal
t‘irtings and t~urnishings within the airplane can be cleaned
with
for
most
commercial metal
applicution;
then
polish
polishes.
to
cloth. Protect the finish with
a
Use
a
soft, clean
brilliant
gloss with
good grade of wax.
a
a
tou
dr;
handbook A2-01335 included in the loose tool and
LEATHER UPHOLSTERY
equipment bag.
CAUTION
Leather upholstery should be kept waxed for maximum
protection. For cleaning, a nonabrasive, chemically neutral,
nonreactive, emulsion type c leaner of cream- like consistency
Do
gasoline, benzene, acetone, carbon
tetrachloride, fire extinguisher fluid, deicinn
fluid, Lacquer thinners, dry cleaning fluid,
window sprays or kitchen scouting compounds
I
511
not use
is recommended. Dilute the cleaner with water, and
the dirty surface with a sponge or soft cloth (use
over
apply it
gentle
a
do not scrub). The solution should nor be
stand, but should be wiped off before drying.
wiping motion,
allowed
to
2-12A
APPROVED SPARK PLUG AND GAP SETTING CHART
Correct
Torque for all Spark Plugs is 320
to
380 in. Ibs.
SPARK PLUG MANUFACTURER AND TYPE
ENGINE: 1O-470-L
A.C.
CHAMPION
REB37N
HSR86L
RHB37N
HSR87LP*
RHB38E
AC271
RHB36P"
AC281
RHB32N
RHB33E
ENGINE: 1O-520-C
IO-520-CB
IO-550-C
RHB32N
AC271
RHB33E
AC281
AC273
AC283
*Indicates fine wire platinum electrodes.
Gap setting is .018 .022 for all spark plug types listed.
provide improved starting and idling characteristics.
Wide gap
(.018
to
.022) spark plugs
NOTE
Heat range is progressively colder as you read
down each column corresponding to the
manufacturer’s
spark plug type.
Where
more
heat range is listed, the colder type is
recommended unless extended low power
operation or engine condition results in spark
than
one
plug fouling.
E-8
2-13
TABLE OF TI-IREAD LUBRICANTS
SYSTEM
MA TERIA L
SPECIFICA nONS
VENDOR PRODUCTS
Any product conforming to
specification
the referenced
may be used.
Fuel
Anti-Seize, Graphite
MIGT-5544
Petrolatum
Armite
Product, Armite Laboratories, Los Angeles,
Calif.
Anti-seize
Compound I,
Esso
Standard Co.
Oil, Manifold
Pressure
Anti-icer, Vacuum
Lubricating
Crease (Gasoline and Oil Resistant)
MIGGd032
G237, Lehigh Chemical Co.,
Chestertown, Maryland
Rockwell 950, Rockwell Mfg.
Co., New York, N.Y.
Royce 32, Royal Eng. Co.,
Whippany, N.J.
Brake, Deicer, Static
Anti-Seiie
and Pitot
White Lead Base
Compound
Federal
Specification
TT-A-580
Armite Product, Armite Laboratories, Lus Angeler,
Calif.
Oxygen
Thread
Compound,
MIGT-5542
Anti-Seize and
Sealing,
Oxygen Systems
No. 15 Rector Well
ment
Equip-
Co., Houston, Texas
nag 217 Acheson Colloies
Co., Port Huron, Michigan
Key Abso-Lute, Type B.,
Key Co., East St. Louis,
Illinois
Oxygen, High
Pressure Side
2-14
Ribbon
Only
Sealant
Dope T~uead
MILT-27730
Pennacel
Tape Corp., New
Brunswick, N.J.
CONSUMABLE MATERIALS CHART
Only the basic
number of each Military Specification is included in the Consumable
Materials Chart. No attempt has been made to update the basic number with the letter
suffix that designates the current issues of the various specifications.
Vendors listed
as meeting Federal and Military Specifications are
provided as reference only and are not specifically
recommended by Beech Aircraft Corporation; consequently,
any product conforming to the specification listed may be used.
The products listed below have been tested and
approved for aviation usage by Beech Aircraft Corporation, or by the
vendor, or by compliance with the applicable specifications. Other products that are locally procurable which conform to the
requirements of the applicable Military Specification may be used even though not specifically included herein.
It is the
responsibility of the operator/user
to
determine the
usage of that item. This determination may be made
ITEM
1.
MA TE~AL
current revision of the applicable Military Specification prior
by contacting the vendor of a specific item.
SPECIFICA flONS
Fuel, Engine
to
VENDOfl PF~ODUCTS
100/130 octane (If not
available,
use
115/145)
2.
Oil, Engine
Continental Motors
Corp., Specification
See
Approved Engine Oils Chart
No. MHS-24B
3.
Corrosion Preventive
MIL-C-6529
Compound
Type
II
Anti-Corrode No. 205,
Cities Service Oil Co.,
60 Wall Tower,
New York
5, N.Y.
Rust Foil No. 652-2,
Franklin Oil and Gas Co.,
Bedford, Ohio
Kendex No. 7038,
Kendall
Refining Co.,
Bradford, Pa.
4.
Lubricating
Oil
MIL-L-6081
Castrolaero 1010
Castrol Oil, Inc.,
CastrolLimited,
254-266 Doremus Ave.,
Newark, N.J.
Kendex7042,
Kendall
Refining Co.,
Bradford,Pa.
Royco 460,
Royal Lubricants Co.,
River Road,
Hanover, N.J.
5.
Lubricating Oil
SAE 20
6.
Lubricating Oil, Aircraft
Reciprocating (Piston Engine)
MIL-L-6082
Conoco Aero Oil No. 1065,
Continental Oil Co.,
Ponca
E8
City, Oklahoma
2-15
CONSUMABLE MATERIALS CHART
ITEM
MATERIAL
(Cont’d)
SPECIFICATIONS
VENDOR PRODUCTS
Phillips 66
Aviation Engine
Oil, Grade 1065,
Phillips Petroleum Co.,
Bartlesville, Oklahoma
Or any approved aircraft engine oil
(graded at 1100 or 1065)
7.
Lubricating Oil(Gear)
MIL-L-2105 Grade 75
Mobilube SHC,
Mobil Oil Corp.,
or
101-380016-1
8.
Lubricating Grease (General
Purpose) (Superseded by
Shoreham
Building,
Washington, D.C.
MIL-G-7711
MIL-G-81322)
9.
Lubricating Grease (High
Temperature)
**MIL-G-81322
Mobilgrease 28,
Mobil Oil Corp.,
Shoreham Building,
Washington D.C.
Aeroshell No. 22,
Shell Oil Co.,
50W 50th Street,
New
Lubricating Grease (Gear)
Mobil
Compound G.G.
or
Mobil 636
York,
N.Y.
Mobil Oil
Corp.,
Building,
Washington, D.C.
Shoreham
11.
Lubricating Grease (Aircraft
**MIL-G-23827
and Instruments, Low and
Supermil Grease
No. A72832,
American Oil Co.,
910 South Michigan Ave.,
High Temperature)
Chicago,
Ill. 60680
Royco 27A,
Royal Lubricants Co.,
River Road,
Hanover, N.J.
Shell 6249 Grease,
Shell
OilCo.,
50 West 5Oth St.,
P.O. Box 95,
New York, N.Y. 07936
12.
Lubricant
Molybdenum
Disulfide Powder
MIL-M-7866
Molykote Z.
Wilco Co.,
Wichita, Kansas
Molykote Z,
Standard Oil of
Kentucky
Molykote Z,
Hafkel Seals,
Glendale, California
2-16
E8
CONSUMABLE MATERIALS CHART
ITEM
(Cont’d)
VENDOR PRODUCTS
SPECIFICATIONS
MATERIAL
Moly-Paul
No. 4,
K.S. Paul Products Ltd.,
Nobel Road,
London, England
13.
Hydraulic
Brayco 756D,
Pray Oil Co.,
MIL-H-5606
Fluid
3344 Medford Street,
Los
Angeles 63, California
TL-5874,
Texaco, Inc.,
135 East 42nd Street,
New
York, N.Y.
FED 3565,
Standard Oil Co. of California,
225 Bush Street,
San Francisco 20, Calif.
Leak
Testing
14.
Oxygen System
Compound
15.
Solvent, Dry Cleaning
White
or
MIL-L-25567
PD680
or
British
Specification 245
Spirit
SAE 10
16.
Lubricating Oil
17.
Aviator’s
18.
Naphtha
TT-N-95
19.
Methyl Ethyl Ketone
TT-M-261
20.
Toluol
’IT-T-548
21.
Paint Remover
Breathing Oxygen
MIL-0-27210
Turco No. 4260,
Turco Products Inc.,
Los
22.
Epoxy Primer
MIL-P-23377
Angeles, California
Ameron Industrial
Coatings Div.,
P.O. Box 2153,
Wichita, Kansas 67201
23.
EX201G,
Wash Primer
Ameron Industrial
Coatings Div.,
P.O.Box2153,
Wichita, Kansas 67201
24.
Zinc Chromate Primer
MIL-P-8585
25.
Rubber Hose
MIL-H-5593
26.
Oil, Engine Preservative
MIL-L-21260
27.
See Item 12
28.
Lubricating Grease
ENCO ANDOK-B
Humble Oil Co.,
Houston, Texas
E8
2-17
CONSUMABLE MATERIALS CHART
ITEM
29.
(Cont’d)
VENDOR PRODUCTS
SPECIFICATIONS
MATERIAL
CRC-2-26,
Solvent
Corrosion Reactions Consultants,
Inc.,
Philadelphia,
30.
Anti-Icer Fluid
TT-I-735
(Replaces MIL-F-5566)
Pa.
Anti-Icer Fluid,
Sherwood and Co.,
Wichita, Kansas
31.
Coast Pro-Seal and
890B-1/2
Sealer
Manufacturing Co.,
Los
32.
Minnesota
Mining and
Manufacturing Co.,
EC-1675B-1/2
Sealer
Angeles, Calif.
St. Paul, Minnesota
33.
Compound
Mining and
Manufacturing Co.,
Minnesota
EC- 1020
St. Paul, Minnesota
34.
Air Conditkler
Refrigerant
R-12
Racon Inc.
Racon 12
Wichita, Kansas
Genetrol 12
Allied Chemical
Specialty Division,
Morristown, New Jersey
DupontInc.,
Freon12
Freon Products Division,
Wilmington, Delaware
35.
Oil(Air Conditioner
Compressor)
500
Viscosity Suniso
Texaco
Capella
E
No. 5
Virginia chemical and
SmeltingCo.,
West Norfolk, Virginia
Texaco Inc.
135 East 42nd Street,
New
36.
Spray Adhesive
No. 77
Minnesota
Mining and
Manufacturing Co.,
St.
37.
EC2216
Adhesive
York, New York
Paul, Minnesota
Mining and
Manufacturing Co.,
Minnesota
St. Paul, Minnesota
38.
Lubricating Oil
39.
Deleted. Refer to Item 3.
40.
Preservative
Hydraulic
10W30
Fluid
MIL-H-6083
Mobil Oil
Corporation,
150 E. 42nd St.,
New
41.
2-18
Conditioning Refrigerant
(Flushing)
Air
R11
York, N.Y. 10017
Racon Inc.,
Wichita, Kansas
E8
~leechcrrdt
BARON 55 AND 58
SHOP MANUAL
CONSUMABLE MATERIALS CHART
42.
.008inch-thick, 2-inch-wide
Vinyl
Film
Vendor Products
Specifications
Material
Item
(Continued)
Minnesota Mining and
Manufacturing Co., 3M Center,
No.474
Tape
St. Paul, MN 55101
43.
Presstite-Keystone Engineering
Presstite No. 576
Sealant
Co., 3900 Chateau Ave., St.
Louis MO
Acrylic
44.
Adhesive
45.
AdhesivelSealant
PS-30
Cadillac Plastics 8 Chemical
Co., Detroit MI
RN732
Dow
Coming Corporation,
Midland, MI 48640
46.
Mining and
Manufacturing Co., 3M Center,
Minnesota
EC776
Cement
St. Paul, MN 55101
47.
Cement Primer
Bostic 1007P
B.B. Chemical Co., 784
Memorial Drive, Cambridge, NE
69022
48.
Cement
Bostic 1008
B.B. Chemical Co., 784
Memorial Drive, Cambridge, NE
69022
49.
Corrosion Preventive
MIL-C-16173 Grade 2
Braycote 137, Bray Oil Co.,
1925 North Marianna, Los
CA 90032
Compound
Angeles,
50.
Water
Displacement
Lubricant
LPS-1
LPS Research Laboratories
Inc., Los Angeles, CA
CRC 3-36
CRC 3-36, CRC Chemicals
U.S.A., Warminster, PA 18974
WD-40
WD-40
Company,
San
Diego.
CA
Oil Co., 1925
North Marianna, Los Angeles,
CA
Brayco 300, Bray
W-L-800A
51.
Sealer
52.
Thread
5651
Locking Compound
Shnee-Moorhead Chemical
Inc., INing TX
Isocryl Tape
Loctite
Loctite Sealant Grade A
Corp.,
705 N. Mountain
Rd., Newington, CT 06111
53.
Solvent
CRC 2-26
54.
Coating
Alodine 1200, 1200S
55.
Cement
EC750
CRC 2-26, Chemicals U.S.A.
Warminster, PA 18974
or
1201
Amchem Products, Inc., Spring
Garden St., Ambler, PA. 19002
Mining and
Manufacturing Co., 3M
Minnesota
Center
St. Paul MN 55101
56.
Lubricating Grease
Aeroshell Grease 5
Shell Oil Co., One Shell Plaza,
P.O. Box 2463, Houston, TX
77001
815
2-19
aeechcraft
BARON 55 AND 58
SHOP MANUAL
CONSUMABLE MATERIALS CHART
57.
Silicon
58.
Adhesive/Sealant
Vendor Products
Specrflcatlons
Material
Item
(Continued)
MIL-S-8660
Compound
Loctite
Loctite 222
Corp.,
705 Mountain
Road., Newington, CT 06111
59.
Loctite
Loctite 601
Retaining Compound
Corp.,
705 Mountain
Road., Newington, CT 06111
60.
EC-1403
Cement
or
1300L
and
3M Center
St. Paul MN 55101
Minnesota
Mining
Manufacturing Co.,
61.
Enamel
Sunbrite 78-U-1003 Enamel
U-100-C Catalyst
(Sealer)
Sterling Paint and Laquer
Manufacturing Co., 315
Brannon Ave., St. Louis, MO.
63139
62.
Mylar Tape (3/4 inch)
Mylar Mystic
No. 733
Mining
and
3M Center,
St. Paul, MN 55101
Minnesota
Manufacturing Co.,
63.
EC-801 Class A-1/2
Cement
Mining and
Manufacturing Co., 3M Center,
Minnesota
St. Paul, MN 55101
64.
Antiseptic
QS4
Burlin and Company, Inc., 2920
Martindale Ave., P.O. Box
270-8 Indianapolis, IN. 26206 A
2840
65.
Cement
A56B
B. F. Goodrich Co., Akron, OH
44318
66.
Grease
MIL-G-1 0924F
Obtain
RL 100S
ICI Americas Inc., Concord
Plaza, 3411 Silverside Road,
Wilmington DE 19850
67.
Oil
(Air Conditioner)
locally
Virginia KMP, 400 Platinum
Way, Dallas, TX 75237
68.
69.
Air
Conditioning Refrigerant
(Charging)
R-134a
Cleaner, Air Conditioning
AC Flush
locally
Castrol North America,
Products Division,
16715 Von Karman Ave., Irvine,
CA 92714-4918
Specialty
System
70.
Obtain
Refrigerant
Leak Detector
Dye
Trace
Highside Chemicals, Inc.,
10-12 Colfax Ave., Clifton, NJ
07013
71.
Adhesive/Sealant
72.
Locquic
2-20
Primer
Loctite 209
Loctite Corp.
705 N Mountain Rd
Newington, CT 06111-1411
Primer N
Loctite Corp.
705 N Mountain Rd
Newington, CT 06111-1411
515
Qeechcraft
BARON 55 AND 58
SHOP MANUAL
CONSUMABLE MATERIALS CHART
Item
73.
Material
Masking Tape
(Continued)
Specifications
UU-T-106
Vendor Products
3M
Tape
and Industrial
Division, 3M Center St. Paul,
Minnesota 55044
74.
Icex
75.
Age-Master
Compound
Silicone
Coating
No. 1
B.F. Goodrich Company, 500
South Main St., Akron, Oh
44318
B.F.Goodrich Company, 500
South Main St., Akron, Oh
44318
*Aviation
gasoline
100LL
(Blue) Preferred.
100
(Green) Minimum grade.
fX~
Precaution should be taken when using MIL-G-23827 and MIL-G-81322 since these greases contain
chemicals harmful to painted surfaces.
515
2-20 A
LUBRICATION CHART
See
See
ITEM
Figure 2-4 (Model 55 Series)
Figure 2-4A (Model 58 Series)
LOCA TION
LUBRICANT
INTERI/AL
SAE 20
or
SAE 10W30
100 hrs.
SAE 20
or
SAE 10W30
100 hrs.
SAE 20
or
SAE 10W30
100 hrs.
DETAIL A
i.
bh Control column
2.
3.
linkage (18)
Control column head (6)
~h Control column
aileron link
(3)
DETAIL B
1.
Door handle (1)
SAE 20
or
SAE 10W30
100 hrs.
2.
Door latch
(2)
SAE 20
or
SAE 10W30
100 hrs.
3.
Door latch (1)
SAE 20
or
SAE 10W30
100 hrs.
Rudder
SAE 20
or
SAE 10W30
100 hrs.
DETAIL C
i.
pedals (8)
DETAIL D
i.
Landing
b MIL-G-81322
gear motor gear
600 hrs.
box (1)
2.
Landing gear actuator gear
box (1)(When properly filled,
Mobil
the oil level
on a dip stick
through the filler
hole is approximately 1/4
inch)
MIL-L-2105
Landing
SAE 10W30
100 hrs.
SAE 10W30
100 hrs.
door
SAE 20
or
SAE 10W30
100 hrs.
mechanism (3)
SAE 20
or
SAE 10W30
100 hrs.
Compound
Mobil 636
GG
300 hrs.
or
Grade75
inserted
3.
4.
ttt
Nose
gear retract
landing
arms
gear retract
(14)
arm
(1)
DETAIL E
i.
Main
landing
hinges (10)
gear
DETAIL F
1.
E8
Door
latch
2-21
LUBRICATION CHART
See
See
ITEI~
Figure 2-4 (Model 55 Series)
Figure 2-4A (Model 58 Series)
LOCATION
2.
Door handle
3.
Door
LUBRICANT
(1)
SAE 20
hinges (2)
SAE 10W30
or
INTERVAL
100 hrs.
M1L-M-7866
100 hrs.
M1L-G-23827
900 hrs.
VV-L-800A
(Preferred)
100 hrs.
(Preferred)
100 hrs.
DETAIL G
i.
Rudder trim tab actuator
or
5 years
or
5 years
or
5 years
(1)
2.
Rudder trim tab
hinge (1)
LPS-1
CRC 3-36
WD-40
3.
Rudder trim tab clevis (1)
VV-L-800A
LPS-1
CRC 3-36
WD-40
DETAIL H
i.
Elevator trim tab
actuator
M1L-G-23827
900 hrs.
hinge (2)
VV-L-800A
100 hrs.
(2)
2.
Elevator trim tab
(Preferred)
LPS-I
CRC 3-36
WD-40
3.
Elevator
push-pull
rod ends
SAE 10W30
100 hrs.
(4)
4.
Elevator trim tab clevis (2)
VV-L-800A
(Preferred)
100 hrs.
LPS-I
CRC 3-36
WD-40
DETAIL I
i.
Aileron trim tab actuator
L~ MIL-G-23827
900 hrs,
VV-L300A
(Preferred)
100 hrs.
(Preferred)
100 hrs.
SAE 10W30
100 hrs.
(1)
2.
Aileron trim tab
hinge (1)
LPS-1
CRC 3-36
WD-40
3.
Aileron trim tab clevis (1)
VV-L-800A
LPS-1
CRC 3-36
WD-40
DETAIL J
i.
Aileron bell cranks (6)
SAE 20
2.
Aileron
MIL-G-23827
(4)
2-22
push-pull
rod ends
SAE 20
or
or
or
100 hrs.
SAE 10W30
E8
LUBRICATION CHART
See
See
ITEM
Figure 2-4 (Model 55 Series)
Figure 2-4A (Model 58 Series)
LUBRICANT
LOCATION
INTERVAL
DETAIL K
Flap
1.
actuator
(2)
MIL-L-2105C Grade 75
900 hrs.
DETAIL L
Aeroshell 5 (Preferred)
MIL-G-81322
100 hrs.
(4)
or
2.
Main shock struts (2)
MIL-H-5606
100 hrs.
3.
Up lock rollers (2)
(Refer to detailed
MIL-G-81322
100 hrs.
L\ MIL-G-81322
100 hrs.
L\ MIL-G-81322
100 hrs.
box (1)
6 MIL-G-23827
600 hrs.
tt Flap flexible drive shaft
MIL-G-23827
900 hrs.
Main wheel
i.
bearings
LUBRICATION
LANDING
LOCK
OF
GEAR
UP
in
this
ROLLERS
section)
Main gear attach points
4.
(4)
Main gear retract
5.
points
(8)
Main gear torque knee
6.
(10)
DETAIL M
I.
2.
t Flap
motor gear
(2)
DETAIL N
Nose wheel door
1.
hinges (4)
SAE 20
or
SAE 10W30
100 hrs.
(Preferred)
100 hrs.
DETAIL O
Nose wheel
1.
bearings
bhh Aeroshell 5
MIL-G-81322
(2)
or
2.
Shimmy damper (1)
MIL-H-5606
100 hrs.
3.
Nose shock strut (1)
MIL-H-5606
100 hrs.
4.
Nose gear torque knee
h MIL-G-81322
100 hrs.
fittings
MIL-G-81322
100 hrs.
points
MIL-G-81322
100 hrs.
points
MiL-G-81322
100 hrs.
(6)
5.
tttt
Nose gear swivel
(2)
6.
tttt Nose
gear attach
(2)
7.
Nose gear retract
(4)
E8
2-23
LUBRICATION CHART
See
See
Figure 2-4 (Model 55 Series)
Figure 2-4A (Model 58 Series)
Rod end
8.
INTERVAL
LUBRICANT
LOCATION
ITEM
fitting (I)
PIiIIL-C-81322
100 hrs.
h MIL-G-81322
100 hrs.
DETAIL P
Nose
i.
steering mechanism
(6)
DETAIL Q
As
MIL-M-7866
Heater iris valve (1)
1.
Required
NOTES
Any parts
must
that rotate
Number in
1
No lubrication
Lubrication
required
No lubrication
-i- The flap
(metal-to-metal) and have
slide
parenthesis
required TC-251,
track rollers
Flap
or
be lubricated with SAE 20
or
no
other
provision
for lubrication
SAE 10W30 oil.
indicates number of lubrication
points.
TC-344 and after, TE-1 and after.
TC-1093 and after, TE-560 and after.
sealed
(pre-lubed
required
bearings).
TE-301 and after, and TH-1 and after.
motor gear box cannot be lubricated
on
airplane
serials TC-2003 and after, TE- 1084 rind after and TH-773 and
after.
gained at the actuator end of the: flexible drive shaft by
pulling the inner cable from the flexible housing.
:t Lubricate the inner cable of the flexible drive shaft. Access is
removing
tti‘ The
nose
the
retaining ring
gear retract
arm
from the actuator
housing,
then
is located beneath the gear box.
ttti- Lubrication required TH-48il and after, TE-1 and after except TE-301 through TE-98-5.
h Precaution should be taken when
harmful to
painted
ah Lubrication
through
points
using
MIL-G-23827 and MIL-G-81332, since these greases contain chemicals
surfaces.
shown for
airplane
serials TC- 1 and after, TE- I and after, TH- I
see Figure 2-3A.
through
TH- 1?88 and TH- i 390
TH- 1395. For later models with dual control columns,
hah Aeroshell 5 and MIL-G-81322
are
not
compatible
lubricants and must not be mixed.
CAUTION
If the type of grease in the wheel bearings is
thoroughly cleaned before relubrication.
ahai~ Lubricate the aileron
aileron
balls
to
push-pull
push- pull
rod ends in
changed,
make certain that all affected
are
using SAE 20 or SAE 10W30 oil, or remove the
using rv1IL-G-23827 grease. Rotate the rod end e~e
Check the aileron system rigging after reinstallation of the push pull rod
place
at
100- hour intervals
rod assembly, and clean and lubricate rod ends
check for adequate i ubrication coverage.
assembly.
2-24
E1B
DETAIL A
DETAIL D
DETAIL C
DETAIL B
iii
DETAIL
DETAIL E
2
1
1J
t~J1
il
ill
~b
is~c’?ill
f~
3
2
RIGKT AND LER. SIDE
~m
3
1
~fb
´•a´• wEw
3
LEFT SIDE
-YF´•--
3
DETAIL G
DETAIL Q
I 1 ITC-371
F
n
2
DETAIL H
TC-502 THRV TC-1657 AND TE-I THRU
TE-967.
EXCEPT TE-50 AND TE-959
1
3
SIDE VIEW
3
4
3
i\
111
TC-1658 AND AFTER.
LUBRICATION DIAGRAM
A
TE-959. TE-968 AND AFTER
TC-1 THRU
BCD
E
a
F
i;
t~4´•
r;\
1
~3
EXCEPT TC-37(
i.
,I
i,
TS
/II
DETAIL P
1
RIGHT AND LEFT SIDE
DETAIL
DETAILI
121
1
i .4! 1
i
P
U
i~--l 3
NOTE
On
Rush
Alemi(r:
hlpe lubrication fittings,
PM
Midget Flush Noule.
use
P
an
O n
314150~1
i
M
tt:
k
THE NOSE GEAR RETRACT ARH IS LOCATED BENEATH THE GEAR BOX
RIGHT AND LEFT SIDE
tttt
DETAIL O
DETAIL N
lli
DETAIL 44
DETAIL L
7
f~h=
+ttt
53
4
s
3
DETAIL K
2
1
4
tttt
ii
il
il
,c´•,
1I1
i
it
lit
RIGHT AND LEFT SIDE
c~i
RIGHT AND LEFT SIDE
55601-1~
Figure
2-4. Lubrication
TE-1 and
Diagram (TC-1
and
after)
DENOTES AREA OF CHANGE
E-8
after,
lBt
2-25
LU BRICATI O~ DIAGRAM
A
I
I
DETAIL A
I
DETAIL B
DETAIL C
I
CDE
IC~-
Lubricate points shown tor airplane serials’M1 m, M-13BB and TH-1390 thru TH-1395.
Fw Later models with dual control columns. see
Fl,,,
fZ3
2-4A.
1
DETAIL D
O
1
I
DETAIL
F
3
153
3
o"’
2
v
J
I
~s,
3
ii~
~e
ttt
I
DETAIL E
TOP VIEW
I
dblb
RIGHT AND LEFT SIDE
I
i
THE NOSE GEAR RETRACT ARM IS LOCATED BENEATH THE GEAR BOX.
O
DETAIL P
O
DETAIL Q
I
O
SIDEVIEW
DETAIL J
DETAIL I
DETAIL H
DETAIL G
i
TH-1 THRU TH-436
D
RIGHT AND LEF~ SIDE
n
o
ii
i
TH-437 AND AFTER
~3
3
111
~a,
RIGHT AND LEFT SIDE
I
RIGHT AND LEFT SIDE.
DETAIL O
I
~+m
DETAIL N
I
I
DETAIL M
I
DETAIL L
123
~3
ttttt33
DETAIL K
O
O
O
t~
-r,T
C~
1~7
RIGHT AND LEFT SIDE
I
RIGHT AND LEFT SIDE
SBbD~-l
Figure
~LP
2-26
2-4A. Lubrication
Diagram (TH-I
and
after)
DENOTES AREA OF CHANGE
E-8
1
2
OI
O
INDEX
LOCATION
CONTROL COLUMN
POINTS
LUBRICANT
INTERVAL
O
Control column chains
(4)
SAE20 or
10W30 Oil
100 hrs
O
Ball
O´•
Torque shafts
Oil
(10)
bearings
(2)
*Wipe
full
length
MEK Solvent
100 hrs
100 hrs
of square shafts with MEK. these
dry and free of oil.
surfaces to remain
36-604-117
18P
Figure 2-48.
Dual Control Wheel Lubrication
(TH-1389,
TH-1398 and
after)
~SI
DENOTES AREA OF CHANGE
8-8
~t
2-27
SERVICING CHART
LOCA TION
ITEM
SERVICE WITH
INTERVAL
See Oil Grades Chart
Preflight
See Section 13 for detailed
100 hrs.
CHECK
Oil Level
Engine
Battery Electrolite Level
Access door
on
upper
cowling
Utility compartment
Forward
instructions
under baggage floor
Autopilot
Servo Air
Aft of
Accumulator
Upper rear inboard side
engine compartment
Filter
Propeller
(if installed)
Air Conditioner
Compressor
Oil
of
Dry air
nitrogen
or
Refer to Section 10
Suniso No. 5
for location and
Texaco
special
Level
100 hrs.
baggage compartment
partition
instructions
Section 10
Air Conditioner
Refer
Refrigerant
for location and
to
special
instructions
Access
plate
500
or
100 hrs.
As
required
As
required
Capella E,
Viscosity Oil
Refrigerant
No.
12
CHANGE
Engine Oil
on
lower
See Oil Grades Chart
25 hrs. TC serials
100 hrs. TE and
nacelle
TH
Oil Filter
Engine
Access door
on
100 hrs. TE and
side of
TH serials
nacelle
CLEAN
Oil Screen
Engine
Directly
below starter
Clean with solvent and
blow
dry with compressed
25 hrs. TC
serials
air
Fuel Strainers
Clean with solvent and
In wheel wells
blow
100 hrs.
dry with compressed
air
Fuel
Injection
Control
Valve Screen
Access door
on
side of the
Clean with solvent and
blow
naceile
100 hrs.
dry with compressed
air
Heater Fuel
Pump Strainer
In
nose
wheel well
Clean with unleaded gas
and blow dry with
compressed
Heater Fuel Filter
(Prior
to
In
nose
wheel well
TC-1406,
dry
with
100 hrs.
compressed
air
TE-847 and TH-176)
Induction Air Filter
air
Clean with solvent and
blow
100 hrs.
At the base of the induction
Clean with solvent and
air intake
blow
dry
with
50 hrs.
compressed
air
Pressure
Regulator Valve
Screens
Forward of the instrument
panel
on
each side
Clean with solvent and
blow
dry
with
100 hrs.
compressed
air
Pressure System Filter
(Foam) (TE-452 thru
Forward of
engine
rear
baffle
Clean with soap
and water solution
100 hrs.
TE-936, TH-1 thru TH-372)
2-28
E8
SERVICING CHART
(Cont’d)
LOCA TION
SEFIVICE WITH
INTERI/AL
Evaporator Blower
Aft of FS 190.00
Backflow with
Every 100 hrs.
Filters
and fwd of FS 49.00
ITEM
CLEAN
(Cont’d)
pressed
com-
air
(E55) fwd of 39.00 (58)
DRAIN
Main Fuel Cell Drains
Lower side of nacelle
Auxiliary Fuel Cell Drains
Lower
Fuel Strainer Drains
In wheel well
Heater Fuel Filter
In
Preflight
surface
wing
nose
Preflight
Preflight
Preflight
wheel well
TC-1406,
TE-847 and TH-176)
(Prior
to
Static Drain
100 hrs.
beside
upholstery panel
pilot’s subpanel
On
REPLACE
Gyro Central Air Filter
Induction Air Filter
panel
500 hrs.
At the base of the induction
500 hrs.
Forward of instrument
air intake
Autopilot
Servo Air
Aft of the
partition
System
Filter (TE-937 and
after, TH-373 and after
and TC-2003 and after)
Forward of
Pressure
engine
1000 hrs.
baggage compartment
Filter
Annually
rear
or
300 to 500 hrs.
baffle
depending
upon
conditions.
SERVICE
Brake Fluid Reservoir
Forward
utility compartment
Hydraulic
Main and Nose Landing
Gear Struts
Top of each
Shimmy Damper
Nose
prior
to
serial
100 hrs.
Fluid
MIL-0-27210
Located behind the cabin
aft bulkhead
and
MIL-H-5606
gear
Hydraulic
Oxygen Cylinder
100 hrs.
MIL-H-5606
strut
Required
Fluid
Hydraulic Fluid
Compressed Air
landing
As
MIL-H-5606
As
Required
Aviator’s Oxygen
TC-502, TE-I and after, and
TH-I and after, the cylinder
E8
is located in the forward
utility
compartment of the
section.
nose
2-29
APPROVED ENGINE OILS
BRAND
COMPANY
Phillips
Phillips Petroleum Company
66 Aviation Oil, Type A
XIC Aviation Multiviscosity Oil
SAE 15 W/50
XIC Aviation Multiviscosity Oil
SAE 25W 60
Shell Oil Company
Aeroshell OilW
Continental Oil
Conoco Aero S
Texaco, Inc.
Texaco Aircraft Engine Oil
Premium AD
Mobil Oil Company
Mobil Aero Oil
Castrol Limited (Australia)
Castrolaero AD Oil
Pennzoil Company
Pennzoil Aircraft
Sinclair Oil Company
Sinclair Avoil
Exxon
Quaker
BP Aero Oil
Corporation
State Oil
Quaker State
Refining Company
AD Aviation
Delta Petroleum Company
Delta Avoir Oil
Union Oil Company of California
Union Aircraft
Gulf Oil
Oil
Exxon Aviation Oil E E
Company, U:S.A.
BP Oil
Engine
Engine
Engine Oil
Oil HD
Gulf pride Aviation AD
Company
Red Ram X/C Aviation Oil 20W-50
Red Ram Limited (Canada)
NOTE
This,chart
meeting
lists
the
Specification
Any other oil
oils
whichjwere
known
to
be certified
as
of Continental Motors Corporation
MHS-24B at the time this manual was published.
which conforms to this specification may be used.
requirements
E8
2-30
SEALING CHART
ITEM
i.
2.
PRODUCT
A56B Cement
EC870 Glue
VENDOR
B.F. Goodrich
Mining and Manufacturing Co.,
Paul, Minnesota
Minnesota
St.
3.
Permatex Sealer No. 2
Permatex
4.
Presstite Sealer No. 576
Presstite
5.
Siiastic Sealer No. 140
Dow
ES
Co., Akron, Ohio
Co., Inc., Kansas City, Kansas
Engineering Co.,
St.
Louis, Mo.
Coming, Midland, Michigan
2-31
SECTION
A I R F RA NI E
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Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
a
L25
3.885
i !oq
STATIONS DIAGRAM
79. 150
)5 25(1’
61.850
25. 500
85.000
54.000
39.315
000
3~h030
11
’13(10(1
70 3(0
9(.813
129.150
I~B
L1S.831
Ipl.OBO
2.1(100
8i5
/123
171 Z.I
113.172
182
lb~:3D5
I:
83.541
1 155.004’
91. 091
.ML FRONT SPII
55.301
153.000
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.150
n
FCSEL*CL: ST~
213.150
36:900
80.260
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60.310
95.063
ooo
15.110
Iii i
3.90(1
36.150
6.200
--J--PRONTSP*R
HORIZONTAL STABILIZER
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a
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31.150
WING
-~L
Z2.250.-~_
o.s,s
oou.aaa
j-
-i
U~L I~ILWO
VERTICAL STABILIZER
81.9
12.25
58.00
8225
12115
Iss.w
I~o.oo
106.aS123."$
-r:
WLIW.W
---E
I
I---
I
-~-1
I
F___
__
I
I
I
KEEL
~3
--~-r---l
27200
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-80.011
-10:00
sz.sbo
83.090
1700
39.W
118.50~´•´•I
10000
1JI:w
179.00
151’.00
I7d.0o
68.00
I9d.00
207.00
213)0
58.00
FUSELAGE
es4a3-3
Stations
Ei8
Diagram (TH-1
Figure 3-3
and
After)
3-3
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
:0-1
~3n
s
r
I
11
15
11
li~n
i. Elevator trim tab actuator
Elevator trim tab actuator
9. Landing gear actuator
10. Control cable pulleys and
sprocket
retract idler
3. Elevator tab cables
4. Horizontal stabilize- mounting bolts
5. Heater ignition, iris valve and blower
assembly
6. Tail cone
7. Elevator bellcrank, elevator down spring,
and turnbuckles
8. Cable
inspection
Fuselage
3-4
5
1.3
2.
Access
rl.
12.
13.
14.
Hinge
nose
5
gear
arm
bolts for
nose
wheel strut
Rudder tab actuator
baggage door
baggage compartment
Nose
Aft
15.
Nose gear retract idler
16.
.Inck attach Iloinl
Openings (TC-1 and After;
Figure 3-4
TE-1 and
arm
(TE-1 altd afler)
55-157
After)
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
2
3
II
1
1
3
2
~1
I
1
n4t
rr-~-T-----I
~3
s1CJiIc~i
I
I
b
)I
4
16
15
Il
Ib
13
9.
i. Elevator Trim Tab Actuator
2. Elevator Trim Tab Actuator Sprocket
3. Elevator Tab Cables
4. Horizontal Stabilizer Mounting Bolts
5. Heater Ignition, Iris Valve and Blower assembly
6. Tail Cone
7. Elevator Dellcrank, Elevator Down Spring,
and Turnhuckles
8.
Cal,le
Inspection
Fuselage
E18
Access
5
Il
5
Landing Gear Actuator
10. Control Cable Pulleys and Nose Gear
Retract Idler Arm
11. Hinge Bolts for Nose Wheel Strut
12.
13.
14.
15.
Rudder Tab Actuator
Nose Baggage Door
Cargo Door
Nose Gear Retract Idler Arm
16. Jack Attach Point
Openings (TH-1
Figure 3-5
and
ss-lj;e
After)
3-5
Ray~hean Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
s
t
LEFT WING
5
a ?6
n
rf!
I
2
(TOP)
n_
to
I
!e
CCI~
2) 1?
14
RIGHT WING
i.
a
I
iT
17
i6
it
iZ1Z1
iO
25
23
(BOTTOM)
LEFT WING
Auxiliary fuel ceil filler neck
Propeller accumulator, voltage
IS.
Removable cowl
nose
7.
engine plumbing
Auxiliary fuel cell transmitter
8.
Aileron bell crank
24.
Aileron tab
Auxiliary fuel cell transmitter
Wing tip spar fitting
Auxiliary tank siphon valve
25.
Wing tip
12.
Auxiliary tank
27.
Main fuel cell transmitter
13.
Firewall terminal bus
(starter relay left hand only)
28.
39 gallon tank)
Pilot mast access
14.
Cowl Flap
29.
Extended range tank filler
regulator
3.
"4.
and alternator fuse
Oil level indicator
16.
panel
access
Main fuel cell filler neck
5.
Main fuel cell transmitter
6.
Nacelle inspection
plate
and
access
to
**9.
10.
II.
(BOTTOM)
cap
Wing leading edge cap
17. Wing mounting bolts
18. Flap access
19. Aileron cable inspection
20. Aileron cable inspection
21. Aileron cable pulley
22. Auxiliary lank access
23. Aileron cable inspection
2.
10
11
f~D3
14
Is
11I
it
i5
(TOP)
n
1~
12 28
tt
RIGHT WING
7
J)
to
26 27
26.
pulley
Main fuel cell filler neck
39
access
actuator and
access
(optional
gallon tank)
(optional
**Removed TC-1847 and after, and
TE-1039 and after.
Wing
3-6
Access
’25 Gallon Main Fuel Cell Installation.
Openings (TC-I
Figure
and
TH038
sn747nn
After; TE-1 and After)
3-6
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
3
29
27
1
26
3
f~-l
n 4
4 ~h
1
31
9
(TOP)
1
9
12
11
)1
7
a
6
Is
16
Il
P
30
3P
?9
RIGHT WING
(TDP)
a Ir
1I
10
n
30
1
~D3
I
21
19
LEFT WING
1
it
:5
X
22
iO
1’7
i3
25
RIGHT WING
(BOTTOM)
7.
inspection plate and access
engine propeller accumulator
Pressure regulator
Wing leading edge cap
Wing mounting bolts
18.
Flapaccess
19. Aileron cable inspection
20. Aileron cable Inspection
21. Aileron cable pulley
22. Auxiliary tank access
23. Aileron cable inspection
8.
Aileron bell crank
24.
Aileron tab actuator and
9.
Fuel cell transmitter
25.
Wingtip
10.
11.
Wing tip spar fitting
Fuel cell siphon valve
12.
13.
Fuel.cell access
Firewall terminal bus
(starter relay left hand
14.
Cowlflap
26.
27.
28.
29.
30.
31.
15.
Removable cowl
i.
Fuel transmitter
2.
3.
4.
5.
Wing
6.
Nacelle
ice
(BOTTOM)
16.
17.
light and relay
Oil level indicator access
Fuel transmitter
Main fuel cell transmitter
to
nose
Wing
E18
2Pi
2! i
n 2
I
30
LEFT WING
21
3
J1
only)
Fuelfiller
opening
Main fuel cell transmitter
Pitot mast
access
Navigationlight
Landinglight
Nacelleaccess
cap
Access
pulley
access
Openings (TH-1
Figure 3-7
and
THOJB
s41748nn
After)
3-7
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING
WING TIP REIMOVAL
a.
Remove the fasteners
(STANDARD)
attaching
wing (screws prior
after and TH-680 and after).
wing tip
the
rivets TC-1916 and after, TE-1071 and
to the
to
TC-1916, TE-1071 and TH-680; blind
NOTE
Airplane serials TC-1916 thru TC-1921, TE-1071 and TE-1072, and TH-703
screws in the upper and lower wing tip tabs which must be removed.
b.
Disconnect the electrical leads to the
WING TIP INSTALLA ~ION
navigation tight and
the
thru TH-707 have
landing light (if installed).
(STANDARD)
a.
Attach the electrical leads to the
b.
Position the
wing tip to the wing
navigation light
and the
landing light (if installed).
(screws prior to TC-1916, TE-1071,
after).
and install the fasteners
TC-1916 and after, TE-1071 and after, and TH-680 and
and TH-680; rivets
~ZIET WING TIP REMOVAL
a.
Disconnectthe
b.
Drainthefuelfromthe
c.
Remove the
d.
Disconnect the electrical leads to the
e.
Disconnect the fuel interconnect and vent lines from the wing
f.
Remove the blind rivets
battery.
access
airplane.
panels adjacent
attaching
to the
the
wing tip.
navigation light.
wing tip
to the
tip.
wing.
CIVET WING nP INSTALLATION
and install the rivets.
a.
Position the
b.
Connect the fuel interconnect and vent lines to the
c.
Connect the electrical leads to the
d.
Refue\the
e.
Check the fuel line connections for leaks.
f.
Install the
g.
Connectthe battery.
3-8
wing tip
wing tip.
navigation light.
airplane.
access
panels.
618
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING REII/1OVAL
a.
Drain all fuel from the
b.
Remove the front seats and side panels.
c.
Remove the
d.
Remove the wing bolt
e.
Place the airplane on a three point jack and raise until the wheels are clear of the
ground. Refer to Section 2 for
instructions. A three point jack should be used because of the unbalanced condition of the
airplane after the
jacking
wing is
f.
rear
seat
airplane.
panel.
from the
access covers
wing.
removed.
Place
a
will also be
suitable cradle under the
required
to assure
wing being
stability.
removed and
a
wing
stand under the
opposite wing.
A tail stand
g.
Disconnect and cap off brake lines at root rib.
h.
Retract the
i.
Disconnect the inboard door
j.
Disconnect the
landing
gear uplock cable at the idler
k.
Disconnect the
landing
gear actuator rod from the V brace in the wheel well.
i.
Disconnect the aileron cables at the turnbuckle in the wheel well and remove the roll
pins from inboard aileron
pulley brackets. Disconnect aileron tab cables and aileron tab stops in left wheel well.
landing
gear until the inboard
actuating
landing
gear doors
are
fully
open.
rod from the control horn.
arm
in cabin.
cable
m.
Disconnect fuel lines between
n.
Disconnect the
o.
Remove the lower aft nacelle
p.
Remove the
leading edge
q.
Remove the
clamps securing the wiring bundles
at terminals located
flap
on
wing
root rib and the
drive shaft at the motor and
fuselage.
remove
the
clamps attaching
the shaft to the
fairing assembly.
cover
of the
wing located between
to the
the
fuselage
and nacelle.
wing inboard leading edge. Disconnect wiring bundles
aft side of nacelle firewall.
r.
Disconnect wiring to the electrical components located in each side of the
upper nacelle.
s.
Disconnect the
t.
Disconnect flap wire bundle and
(booster
plumbing between
pump and fuel
the
Remove the
v.
Disconnect the pitot line between the
w.
Using
E18
clamps securing engine
grease
wing
root rib and the
fuselage.
safety switch wiring in left wheel
quantity transmitter) in each wheel well.
u.
a
fuselage.
controls to
wing
well. Disconnect
plumbing
and electrical
wiring
leading edge.
root rib and the
pencil, outline the position of the wing
on
fuselage (left wing only).
the
fuselage.
3-9
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
I CAUTION I
no bolt binding during removal. Should binding occur, adjust the wing position until
disengages freely. Do not screw or drive a bolt in or out of the fittings.
There should be
the bolt
attach bolts from the
x.
Remove the
wing
y.
Remove the
wing by pulling
it
fittings.
straight away from the fuselage.
NOTE
Discard the
I
mounting
nuts. Install new
mounting
nuts when
the
installing
Discard the soft aluminum washers installed between the upper
wing is installed.
wing
wing.
attach
fittings.
Instali
new
washers when the
WING PANEL LEADING EDGE REMOVAL
a.
Supportthewingon
asuitablecradle.
NOTE
The entire nacelle must be removed
prior to
removal of the
leading edge.
b.
Remove the
c.
Disconnect the fuel lines and
d.
Remove the
wing tip (see wing tip removal).
e.
Remove the
screws
attaching
the forward section of the outboard rib to the spar.
f.
Remove the
screws
attaching
the
g.
Remove the machine
h.
Assure that the aft
portion
i.
Remove the
wires
access
hinge
doors.
screws
remove
the fuel cell.
nose
skin to the front spar at the
that attach the root
of the
wing panel
is
nose
wing
root.
rib to the front spar.
adequately supported.
(Clamp vise grip pliers on the hinge wire
and
using the pliers
as
both fulcrum and lever,
pull).
CAUTION I
I CAUTION
Do not attempt to spin the
will cause it to seize in the
j.
Remove the
3-10
hinge wire out with
hinge and break.
a
drill motor; the
heating
and
expansion
of the wire
wing panel leading edge.
E18
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING PANEL LEADING EDGE INSTALLATION
NOTE
Before
assembling the spar to the wing section, drive a hinge wire through the sections
foreign matter and to assure that no areas of excessive binding exist.
to
remove
burrs and
a.
Use
b.
Support
c.
Insert the
d.
a
hinge
wire coated
liberally
the aft section of the
hinge
wire into the
Drive the hinge wire using
telescoping guide.
the
a
with
Molybdenum
wing panel
and
attaching hinge,
align
as
telescoping guide
Disulfide
the
far
as
(12,
Consumable Materials Chart, Section
2).
leading edge hinges.
possible by
hand.
tube and rivet gun. As the wire is driven in
remove
sections of
I CAUTION I
Do not attempt to
spin the hinge pin with a drill motor as the heat and expansion may cause
the wire
to seize and break.
NOTE
Use Kit No. 35-5888 when
tube
firmly against
e.
Install the machine
f.
Install
g.
Install the
h.
Connect the
i.
Install the
j.
Connect the electrical
k.
Install the nacelle.
i.
an
screws
the
screws
attaching
screws
installing the hinge wire. To prevent kinking
hinge throughout the entire driving procedure.
that attach the root
the
attaching
nose
that attach the
wiring
wing tip
to the
larger
rib to the front spar.
to the
wing tip.
wing.
landing light.
Cement the rubber fillet to the root of the
wing, using
cement
(55,
Consumable Materials Chart, Section
2)
or
cement.
m.
Install the fuel cell and connect the fuel lines.
n.
Install the
E18
hold the
skin to the front spar.
wire and install the
equivalent fuel resistant rubber
access
hinge wire,
the forward section of the outboard rib to the spar.
navigation light
screws
nose
of
doors.
3-11
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING INSTALLATION
NOTE
When
replacing wing bolts make sure that the replacement bolts have been properly inspected usmagnetic particle process. Bolts must be magnetically inspected before installation as wing
bolts. Bolts may be acquired through Raytheon Aircraft Parts Inventory and Distribution (RAPID).
The individual placing the order must stipulate the need to have the bolts inspected before
ing
the
shipment.
nonmetallic brush and solvent (18 or 19, Consumable Materials Chart, Section 2), clean the wing attach
fittings
(bolts, washers and nuts). Inspect the wing attach fittings and hardware as instructed under
WING BOLT, NUT, AND FITTING INSPECTION.
a.
Using
a
and hardware
WARNING
IWARNING
Wing
I
bolts that have reached their life limit
be reused. See Chart 1.The
b.
Coat the
fitting
bolt bores and
mounting
(10
years after the initial
replaced at each
nuts must be
bearing faces, bolts, washers,
2).
inspection), must not
inspection interval.
and nuts with corrosion
preventive compound (49,
Consumable Materials Chart, Section
CAUTION I
I CAVTIOW
Each bolt must be inserted
the
c.
wing
Move the
until the bolt
wing
into
by hand without binding.
freely in the fittings. Do
moves
position
and
align
the
wing fittings
If a bolt cannot be
not
screw or
with the
easily inserted, reposition
fittings.
drive the bolt into the
carry-through fittings.
Insert the bolts into the
fittings.
CAUTION 1
I cnuTloN
Bolts, washers and nuts must be oriented as shown in the applicable figure for each location
(Figures 3-8, 3-9, 3- 10, and 3- 11.
d.
Start the nuts
drawn
on
bolt bore. If
e.
on the upper forward and aft bolts. Rotate the wing trailing edge until alignment with the outline
fuselage is realized. After rotation is established, verify that the lower forward bolt is not binding in the
bolt binding is encountered, adjust the wing until the bolt moves freely.
the
Tighten
the upper forward and aft nuts.
CAUTION I
I cnuTloN
Prior to
torquing
the lower aft nut,
a
slight gap
may be evident between the fittings. This gap should
torquing the lower aft nut.
not exceed 0.060 in width. No gap should remain after
3-12
E18
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
f.
Torque the wing nuts in the following order: Upper forward, upper aft, lower forward and lower aft. When a torque
adapter is used, the length of the adapter must be added to the length of the torque wrench and the proper
value
computed as detailed in Section 1. Coat the bolt threads that protrude through the nut with corrosion
torque
preventive compound (49, Consumable Materials Chart, Section 2).
wrench
I
CAUTION
cnu-rlou
I
When torquing the wing bolts, assure that ‘the wing bolt wrenches do not bottom out on the wing
fittings. Such an occurrence could cause false torque readings and damage the fittings. After torquing the upper forward wing attach bolt, remove the holding force from the wing cradle prior to torquing the remaining three bolts.
g.
Install the
engine
and connect the
engine
controls. Install the
clamps that secure
the
engine
controls to the lead-
ing edge.
h.
Connect the
plumbing
i.
Connect the
plumbing and wiring in the wheel well. Connect the aileron cables and install the roll pins
pulley brackets. Connect the aileron tab cables and aileron tab stops (LH only).
between the
wing
root rib and the
fuselage.
in the
inboard aileron cable
j.
on
k.
Connect the landing gear actuator rod to the V-brace in the wheel well and install the inboard door
the inboard door control horn.
Connect the
securing
wiring
to the electrical
the wire bundles to the
and connect the
wiring
to the terminals on the aft side of the firewall.
Install the
m.
Connect the
flap
n.
Connect the
uplock cable
o.
Fill the brake reservoir with hydraulic fluid and bleed the brake system.
p.
Remove the stands from under the
q.
Installthewing
Install the
s.
Test
E18
rear
cover
rod
components located in each side of the upper nacelre. Install the clamps
leading edge
i.
leading edge
actuating
between the
fuselage
and nacelle. Install the lower aft nacelle
drive shafts at the motor and install the
clamps
that attach the shafts to the
fairing assembly.
fuselage.
at the inboard floor idler arm in the cabin.
wing
and tail and take the
airplane
off the
jack.
boltcovers.
seat
fly the airplane
panel, side panels and
to assure proper
front seats.
wing and stall warning
vane
adjustment.
3-13
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
105090A032-12K WASHER
t95-110025-1 WASHER
WITH RADIUS
TOWARDS WING FITTING)
(POSITION
EB126 NUT (EXTERNAL WRENCHING)
2359 AND’AFTER, TE-1183 AND AFTER.,
TH-1193 AND AFTER)\
+95-110021 WASHER (POS(TION
WITH COUNTERSINK TOWARDS
BOLT HEAD)
_
NAS152-37/M/ BOLT:
OR
131790-1 BOLT
WING
~-1
TFUSELAGE
FITTING
DRAIN HOLE
+tMS20002-12 WASHER
WET BOLT TORQUE: 2480 TO 2600 INCH-POUNDS COAT THE COMPLETE BOLT. NUT,
WASHERS, WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MIl-C-16173,
GRADE 2 CORROSION PREVENTIVE COMPOUND.
tCHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS.
*~MS20002-12 WASHERS MAY BE USED AS REQUIRED BETWEEN THE NUT AND 95-110025-1
WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT.
12NB126NUT (INTERNAL WRENCHING
(TC-1 THRU TC-2353, TE-1 THRU
TE-1182, TH-I THRU TH-h192)
O
O
o
f~i
I, o
DETAIL
A
5C31-2B
Upper
3-14
Wing Bolt
Figure 3-8
Forward
Installation
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
105090A032-1 OJ
WASHER
+95-110025-3 WASHER
(POSITION WITH RADIUS
TOWARDS WING FITTING)
35-1051 11 WASHER
(TC-I THRU TC-2128.
TE-1 THRU TE-1126,
TH-1 THRU TH-912)
35-105111-3 WASHER
(TC-2129 AND AFTER.
TE-1127 AND AFTER,
TH-913 AND AFTER)
12NB108 NUT
DRAIN
HOLE
NAS150-35/M:
BOLT
FUSELAGE FITTING
WING FITTING
*tNAS143-10 WASHER
WET BOLT TOROUE: 1180 TO 1300 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT,
WASHERS. WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MIL-C-~6173.
GRADE 2 CORROSION PREVENTIVE COMPOUND.
+CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS.
*+NAS143-10 WASHERS MAY BE USED AS REOUIAED BETWEEN THE NUT AND 95-110025-3
WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT.
ol, o
55-3127
Upper
E18
Aft
Wing Bolt Installation
Figure 3-9
3-15
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
o
I,
o
NAS495-14-26 80LT
WING
THFIU TC-1442, TE-1 THRU TE-862,
TH-1 THRU TH-234)
(TC-1
FITTING
1317903 BOLT
(TC-1443 AND AFTER,
TH-235 AND AFTER)
TE-863 AND AFTER,
1F’
88144
or
2881845-144 NUT
+50-105011 WASHER
FUSELAGE FITTING
(POSITION WITH RADIUS
TOWARDS WING FITTING)
WET BOLT TORQUE: 2880 TO 3000 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT, WASHER.
WING FITTING BOLT BORES, AND EXPOSED THREADS WITH MIL-C-16173. GRADE 2
CORROSION PREVENTIVE COMPOUND.
+CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS.
55-31-29
Wing Bolt Installation
Figure 3-10
Lower Forward
3-16
E18
RayZheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
o
I,
o
95-110021-1 WASHER (POSITION
COUNTERSINK TOWARDS
BOLT HEAD)
rWITH
NAS143-12 WASHER
12N8126
(INTERNAL WRENCHING)
NUT
OR
LH6422T126
(EXTERNAL WRENCHING)
NUT
MS21 250-1 2-024/M/
+95-110025-1 WASHER
(POSITION WITH RADIUS
TOWARDS WING FITTING)
BOLT
BOLT TORQUE: 2480 TO 2600 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT,
WASHERS, WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MIL-C-16173,
GRADE 2 CORROSION PREVENTIVE COMPOUND.
WET
+CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS.
t+ NAS143-12 WASHERS MAY BE USED AS REQUIRED BETWEEN THE NUT AND 95-110025-1
WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT.
55-31-26
Lower Aft
E18
Wing Bolt Installation
Figure 3-11
3-17
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ADJUSTING THE WING
After installation of
of attach of either
a.
Raise the
its lift
as
a
or
wing, or repairs to it, flight tests may show one wing is chronically heavy.
wings to correct the difference, using the following procedure:
If so, alter the
angle
both
trailing edge of the light wing
to decrease its lift or lower the
trailing edge of the heavy wing
to increase
follows:
1.
Using
2.
Place the
a
grease
structions. Place
pencil,
airplane
position
of the
wing
on
the
fuselage.
point jack and raise until the wheels gre clear. See Section 2 for jacking inwing being adjusted and a wing stand under the opposite wing. A tail
stability.
three
suitable cradle under the
a
stand will also be
on a
outline the
required
to assure
on the lower wing attach bolts and remove the bolts and nuts from the upper wing attach
bearing faces and bolt bores of the fittings, the complete bolt, washers, and nut with corrosion preventive compound (49, Consumable Materials Chart, Section 2). install new soft aluminum washers between the
upper wing attach fittings. Install the bolts, washers and nuts into the fittings. Raise or lower the trailing edge as required and torque the wing attach nuts in the following order: upper forward, upper aft, lower forward, and lower aft.
There should be no gap between the fittings after the last nut is torqued. Torque each nut to the wet torque value
shown in the appropriate illustration (Figure 3-8, 3-9, 3-10, and 3-11). Coat the exposed threads that protrude
through the nuts with corrosion preventive compound (49, Consumable Materials Chart, Section 2j.
3.
fittings.
Loosen the nuts
Coat the
NOTE
After torquing the upper forward wing attach nut,´•
torque the three remaining nuts.
4.
Remove the
wing
and tail stands,
remove
the
remove
the
airplane from
holding force from the wing
the
jack
and test
fly
the
cradle and
airplane.
WING BOLT, NUT, AND FITTING INSPECTION
NOTE
Read the entire section before
removing
any bolts for
inspection.
I WARNING I
The
wing
bolts installed in all
airplanes five years
old
or
older must be removed and
inspect-
ed. If after
inspection the bolts prove to be free of corrosion, cracks and mechanical damage,
installed for an additional five year period at which time another wing bolt inbe
they may
be performed. Ten years after the initial inspection, all wing bolts must be remust
spection
placed
with
with the
new
Wing
hardware. Render unserviceable all components removed in
Inspection And Replacement Chart.
Before removing any wing bolt, draw
realignment, should it be necessary.
a.
3-18
compliance
Bolt And Nut
an
outline of the
wing position
on
the
fuselage
with
a
grease
pencil
to aid
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
5
YEARS
NEW
AIRPLANE
h
5
YEARS
5
1\
5
YEARS
YEARS
FIRST
REPLACEMENT
INTERVAL
SECOND
INSPECTION
INITIAL
INSPECTION
5
5
YEARS
5
YEARS
REPEAT
INSPECTION
AND
REPLACEMENT
CYCLE
YEARS
AIRPLANES
5
YEARS
OLD
OR OLDER
INITIAL
INSPECTION
SECOND
INSPECTION
FIRST
REPLACEMENT
INTERVAL
REPEAT
INSPECTION
AND
REPLACEMENT
CYCLE
NOTE
NOTE
THE FIRST WING BOLT INSPECTION
FOR AIRPLANES FIVE YEARS OLD OR
OLDER MUST BE PERFORMED AT THE
FIRST SCHEDULED INSPECTION FOLLOWING
THE ISSUE DATE OF REVISION E7.
EACH REPLACEMENT INTERVAL.
ALL WING ATTACH HARDWARE
[BOLTS. WASHERS, AND NUTS)
MUST BE REPLACED.
AT
TH038
99299~AA
WING BOLT AND NUT INSPECTION AND REPLACE CYCLE
CHART1
818
3-19
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
CHART 2
WING BOLT WRENCHES AND TORQUE ADAPTERS
POSITION
LOWER FORWARD
BOLT PART
WRENCH PART
NUT PART
NUT TORQUE
NUMBER
NUMBER
NUMBER
ADAPTER
NAS495-14-26
TO-i thru
TE-I thru
TS1222-3
EB144
TC-1442,
TE-862,
50-590014
or
ZEB1845-144
TH-1 thru TH-234.
131790-3
TC-1443 and after,
TE-863 and after,
TH-235 and after.
UPPER FORWARD
NAS152-37 /M1
or
131790-1
TS1222-3
inch
TS 1222-4
inch
(9/16
hex)
12NB126
TO-i thru
(1/2
hex)
TE-I thru
TS1171-2
TC-2358,
TE-1182,
TH-I thru TH-1192.
EB126
TS1176-2
TC-2359 and after,
TE-1183 and after,
TH-1193 and after.
UPPER AFT
NAS150-35 /M/
TS1222-4
12B108
TS1171-1
or
50-590013
LOWER AFT
MS21250-12-024
M/
3-20
TK1817-922-4
12NB126
or
LH6422T-126
TS1171-2
or
TS1176-10
E18
Raythean Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
CAUTION 1
PdAUTION
during removal or installation. Do not drive or screw a bolt in or out
of the fittings. If wing bolt binding is encountered, place the airplane on a three pointjack and raise
the airplane until the wheels are clear (see Section 2 forjacking instructions). Place a suitable cradle under each wing and a tail stand under the aft portion of the fuselage. Defuel the wing, loosen
the remaining bolts and reposition the wing until the bolt moves freely through the fittings. Replace
There should be
no
bolt binding
the soft aluminum washers between the upper fittings and torque the bolts as instructed under
WING INSTALLATION. If bolt binding is not encountered and the wing is not shifted, replacement
of the soft aluminum washers between the upper wing attach fittings is not required.
NOTE
been given
Raytheon Aircraft Company supplies wing attach hardware (bolts and nuts) that have
These components may be identified
an additional magnetic particle inspection since manufacture.
by the green dye on the head of the bolt and on the nut.
WARNING
Iwaanl~ol
THE
components specified in the applicable illustrations. DO NOT INSTALL
BLACK P/N H-20 NUTS, these nuts have been dry film lubricated with molybdenum disulfide.
Use
only
the
When MIL-C-16173 Grade II corrosion
preventive compound
is added to these nuts, the adtightened to the wet
ditional lubrication may cause improper preload in the bolt when it is
torque values specified in Figures 3-8, 3-9, 3-10, and 3-11.
Starting
b.
at
c.
a
at the lower forward
time until the
Using
a
complete
nonmetallic brush,
terials Chart, Section
wing attach point on each side, remove, inspect, and replace
eight bolts and nuts have been inspected.
one
bolt and nut set
set of
thoroughly
clean the bolt washers and nut with solvent
(18
or
19, Consumable Ma-
2).
CAUTION 1
rcnunon
Assure that the 50- 10501 1, 95- 1 1 0025- 1 and 95 1 1 0025-3 washers shown in Figures 3-8, 3-9 3- 1 0,
and 3-11 have a full complete radius with no sharp edges which could mark the fittings. Replace
the washer if it has
an
incomplete
radius
or
sharp edges.
with a
If the bolts and nuts do not exceed the life limit shown in Chart 1, visually inspect each bolt and nut
cadmium
The
plating
mechanical
and
damage.
1 O-power or stronger magnifying glass; inspect for corrosion, cracks,
inof
result
the
are
prevailing
These
areas
usually
may display areas that appear rubbed, discolored or polished.
deteriocadmium
of
because
be
plating
rejected
stallation procedures and are of no significance. A bolt should not
must be
ration; however, any component (bolt, washer or nut) that is cracked, corroded or has mechanical damage
d.
replaced.
circumferential
magnetic particle inspection process described in this chapter, check each bolt for
of all damage
free
crack indications and each nut for longitudinal crack indications. If the bolt and nut prove to be
and
(corrosion, cracks, crack indications, and mechanical damage), they may be reused after demagnetization
e.
Using
the
cleaning.
E18
3-21
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
f.
Clean the spar fitting bolt bores with solvent (18 or 19, Consumable Materials Chart, Section 2). Do not strip the
epoxy paint from this area. Inspect the surface condition of each fitting; focus special attention on the washer seat
and bolt bore area. If scoring, corrosion pitting, or washer impressions are discovered in this area, contact the Tech-
nical
Support Department of Raytheon Aircraft Company. If the fitting is satisfactory, coat the bolt bore and bearing
fitting with coating (54, Consumable Materials Chart, Section 2). Allow the coating to remain on the surface for approximately five minutes. When the five minutes have elapsed, wash the coated areas with water and
blow dry (do not wipe dry). Paint the treated areas with ´•zine chromate primer (49, Consumable Materials Chart, Section 2).
faces of the
g. Coat the bearing faces and bolt bores of the fittings, the complete bolt, washers and nut with corrosion preventive compound (49, Consumable Materials Chart, Section 2).
h.
Install the bolt, washer
or
washers, and
nut into the
wing fittings.
I CAUTION
cAlmoNI
Ensure that the wing bolt wrenches do not bottom out
ous torque readings and damage to the fittings.
i.
on
the
wing fittings.
This could
cause errone-
Torque
the nut to the wet torque value shown in the appropriate illustration (Figure 3-8, 3-9, 3-10, and 3-11).
torque wrench adapter is used, the length of the adapter must be added to the length of the torque wrench
and the proper torque value computed as detailed in Section 1.
When
a
Coat the exposed threads that protrude
j.
Materials Chart, Section
through
the nut with corrosion
preventive compound (49, Consumable
2).
k.
Check that the decal shown in
i.
At the first scheduled
Figure
3-12 is affixed to the
appropriate locations
inspection after the wing bolts have been loosened
and
on
the
torqued
or
airplane.
after initial installation,
check each bolt for proper torque.
m.
Check the drain ports in the upper
3-22
wing
attach
fittings
to
ensure
that
they
are
unobstructed.
E18
Rayl~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
NOTICE
WING BOLTS ARE LUBRICATED
SEE MAINTENANCE MANUAL
FOR CORRECT TORQUE VALUES
WHEN THE CORROSION PREVENTIVE COMPOUND
AFFIX THE ABOVE OECAL TO THE FOLLOWING
I.
ON
THE
SIDE
2.
ON
THE
WING
IMMEDIATELY
FORWARD
OF
THE
LH
3.
ON
THE
WING
IMMEDIATELY
FORWARD
OF
THE
LOWER
4.
ON
THE
WING
OF
THE
FUSELAGE
IMMEDIATELY
AFT
IMMEDIATELY
OF
THE
TO
HAS BEEN APPLIED
LOCATIONS:
ABOVE
LOWER
THE
FORWARD
AFT
RH
FORWARD
WING
AND
AFT
WING
WING
BOLT
AND
FORWARD
WING
THE
BOLT
COVERS
BOLTS.
AFT
WING
BOLT
COVERS
BOLT COVERS.
COVERS
ON
BOTH
ON
BOTH
SIDES.
SIDES.
THI1B
999996A/\
Lubricated Bolt Identification Placard Location
Figure
3-12
MAGNETIC-PARTICLE INSPECTION
Magnetic-Particle Inspection is a method for locating surface and subsurface discontinuities in ferromagnetic materials (i.e. materials capable of being magnetized); consequently, non ferromagnetic materials (such as aluminum
alloys, magnesium alloys, copper alloys, lead, titanium alloys, nickel base alloys and many stainless steel alloys)
cannot be inspected by this method. Magnetic-Particle Inspection is based upon the principle that any discontinuities
lying in a direction generally transverse to the direction of the magnetic field of the part magnetized for the test will
cause a leakage field to be formed at and above the surface of the part. The presence of the leakage field denoting
the discontinuity is detected by the use of finely divided ferromagnetic particles over the surface of the part. Some
of the particles are magnetically gathered and held by the leakage field to form an outline indicating the location,
size, shape and extent of the discontinuity. In general, magnetic particle inspection utilizes a variety of types of
equipment for magnetization, as well as several methods for application of ferromagnetic particles to the test part.
Additionally, the ferromagnetic particles are available in a selection of colors (including fluorescent) and particle
shapes. Magnetic particle inspections required by this manual can best be accomplished by utilizing the wet continuous method on the standard wet horizontal type equipment, with either visible or fluorescent magnetic particles
suspended in a petroleum base vehicle (normally kerosene). Since magnetic particle indications are best obtained
when the discontinuity lies in a direction transverse to the magnetic field, the following procedures are recommended
for optimum detection of discontinuities in both bolts and nuts.
WARNING
JWARNIYGI
Improper operation
faulty equipment or unbeing inspected. Minute electrijeopardize
during inspection by improper operation of the test equipment can
of the
trained operators can
cal are burns caused
magnetic particle inspection
because of
the ainnrorthiness of parts
result in eventual failure of the part.
E18
3-23
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
Bolts: Inspection of a bolt is accomplished by
longitudinal magnetization in
inner diameter of the coil greatly exceeds the bolt
diameter). For
proper
to the coil inside wall with the bolt
is flowed
on
the bolt and the
length perpendicular to
appropriate
current is
applied
the
procedure, laboratory testing has indicated that the ampere
tion of discontinuities
perpendicular to
winding
to achieve
a
multi turn low-fill factor coil
magnetization
the bolt is
(i.e.
positioned
the
close
direction. The
adequate
turn values listed in
magnetic particle suspension
strength. Using the described
Chart 3 provide for optimum detecfield
the bolt axis.
CHART 3
MAGNETIC-PARTICLE INSPECTION (BOLTS)
BOLT
TOTAL BOLT
AMPERE
DIAMETER
LENGTH INCLUD-
TURNS
ING HEAD TO
NEAREST 1/4 INCH
518 INCH
21/21NCH
7,900
5/8 INCH
23/4 INCH
7,100
5/8 INCH
3 INCH
6,600
3/4 INCH
3 INCH
7,900
314 INCH
31/41NCH
7,400
3/4 INCH
31/2 INCH
6,700
314 INCH
3314 INCH
6,300
7/8 INCH
31/21NCH
7,900
7/8 INCH
3314 INCH
7,400
7/8 INCH
4 INCH
6,900
7/8 INCH
5 INCH
5,500
1 INCH
5 INCH
6,300
*Amperage requirement is the ampere turns value divided by the number of turns
the coil. For example: A i-inch diameter x 5-inch
long bolt tested on a 5-turn coil
would require 6,30015, or 1,260 amps.
on
CHART 4 MAGNETIC-PARTICLE INSPECTION
NUT SIZE
CENTRAL CONDUCTOR
(NUTS)
AMPERAGE
SIZE
3-24
518 INCH
1/2 INCH
500 AMPS
314 INCH
5/8 INCH
600 AMPS
7/8 INCH
314 INCH
700 AMPS
1 INCH
7/8 INCH
800 AMPS
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
Inspection of a nut is accomplished by circular magnetization on a central conductor (usually a copper rod)
bar is inserted
the approximate size of the nut inside diameter. For proper magnetization, the central conductor
The
horizontal
particle
the
wet
magnetic
of
heads
the
equipment.
between
is
the
bar
positioned
through the nut and
adachieve
to
conductor
central
the
is
current
and
the
through
nut
the
applied
appropriate
suspension is flowed on
listvalues
that
the
indicated
has
amperage
described
the
testing
procedure, laboratory
equate field strength. Using
ed in Chart 4 provide for optimum detection of discontinuities parallel to the nut axis.
Nuts:
magnetic particle inspection, the parts must be carefully demagnetized
ticles. Examine parts for any possible evidence of electric are burn that may
After
ferromagnetic parduring the inspection.
and cleaned of the
have occurred
WING MAIN SPAR CAP VISUAL INSPECTION
FIGURE 3-13
The
wing
spar cap must be
inspected
for corrosion
annually.
WARNING
IWARNIWO\
All
of the
areas
spar cap, must
wing main spar caps,
be inspected.
from the
wing
attach
fitting
to the outboard end of the
RH spar
Beech Kit No. 58-4002-1S contains the parts and instructions necessary to install a new LH and
ordered
be
must
which
separately.
model 55 and 58 series wing panels. The kit does not contain the spars
on
the
NOTE
extended
Special emphasis should be placed on airplanes that have been operated or stored for
conditions
are
highly conperiods (5 years or longer) in geographical locations where atmospheric
ducive to corrosion.
Inspection
of the upper and lower spar caps should be
accomplished
in the
following
manner:
nonmetallic subExamine the forward and aft sides of the spar cap where it meets the skin. If a whitish, saltlike,
occurred. Wax or paint
stance is noted, a thorough inspection must be performed to determine if corrosion has
corbetween the edge of the skin and the exposed section of the spar cap should not be misinterpreted as
a.
trapped
rosion.
NOTE
To
ure
b.
gain
access to
the upper spar cap in the nacelle area,
remove
the shaded
panels
shown in
Fig-
3-14.
Wash all
exposed
areas
of the upper and lower spar caps.
of the upper and lower spar caps for irregularities, such as paint blisters,
could
raised or uneven areas, and cracks. The exposed areas of the spar caps are extruded flat and irregularities
occurred.
has
if
determine
any damage
be an indication of corrosion. Thoroughly investigate all irregular areas to
c.
Visually inspect
all
exposed
areas
NOTE
Uneven
or
by moving
E18
raised
a
the spar caps may be detected by sliding the fingers over the surface,
surface.
over the surface or by sighting down the length of the spar cap
areas on
straight edge
3-25
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
If unusual conditions
encountered that cannot be resolved
are
Raytheon Aircraft Company for evaluation
locally,
contact the Technical
Support Department
required.
at
and determination of corrective action that may be
THIS ILLVSTRATION REPRESENTS A
TYPICAL SECflON OF THE SPAR CAP
AREAS TO BE INSPEcIED FOR
INDICATORS OF POSSIBLE cORROSHON
THE (NOIcATORS ARE ALL SHOWN IN ONE
BOX SECTION SKIN
AREA AND *RE EXAGGERATED FOR CLARITY
ANY ONE OR ANY COMBIN~TION OF THE
CAUSE FMR FURTHER
INDICATORS
ARE
O
INVESTIOATK)L(
SPAR C~IP
AREAS
e-~
-c~
o
O
~o
o
o
o
o
O
o
-´•E
o
O
LEADING
EDGE
V~
cooJsrJ
O
THIS RIVET PATTERN WILL VARY
ON DIFFERENT MODELS
PAINT
Visual
o
o
o
Spar Cap Inspection
Figure 3-13
o
o
o
LEFT
WING
o
o
(TOPI
RIGHT
WING
(TOP)
C94TC0383030 0
Upper Spar Access Panel
Figure 3-14
3-26
E18
Raythean Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
FUSELAGE
FORWARD CARRY-THROUGH SPAR COVER RE~OVAL
and
copilot
a.
Remove the
b.
Remove emergency
c.
On aft side of spar cover,
d.
On forward side of spar cover,
e.
Remove RH
f.
From inside of RH
g.
Lift spar
pilot
landing
seats.
gear crank
pull back carpet
pull
from spar
cover
and
cover.
remove screws
back carpet and
from spar
remove screws
cover.
from spar
cover.
access cover.
cover
loosen
access cover,
and
remove
clamp and
remove
air duct from
plenum
and
grill assembly.
from forward spar.
FORWARD CARRY-THROUGH SPAR COVER INSTALLATION
I CAUTION I
Improper installation of
the forward
carry-through spar cover may interfere with the landing
landing gear hand crank will engage and rotate
emergency hand crank operation. Ensure the
out interference with the spar cover.
the forward spar.
a.
Center spar
b.
From inside of RH
c.
Install RH
d.
On forward side of spar cover, install
e.
On aft side of spar cover, Install
f.
Check the emergency
the forward
cover on
access cover
g.
Install emergency
h.
Install the
E18
access
carry-through
pilot
cover, install air duct on
plenum
and
grill assembly
and
tighten clamp.
assembly.
landing
spar
copilot
screws
screws
to secure forward end of spar cover and install
to secure aft end of spar cover and install
gear hand crankto
ensure
carpet.
carpet.
handle will engage and rotate without interference with
cover.
landing gear crank
and
gear
with-
cover
to spar cover.
seats.
3-27
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING FORWARD SPAR CARRY-THROUGH STRUCTURE INSPECTION
WITHOUT REPAIR KIT
This
procedure provides inspection and repair information relating
to the forward
wing
spar structure at the forward
and aft frames.
NOTE
The
areas
non
repaired
Remove the
a.
ry-through
b.
in
identified in
structures
pilot’s
and
Figure 3-15 should be inspected for cracking at the intervals specified for
by Chart 5 using the following inspection procedure:
copilot’s
seats and the
carry-through
cover
to obtain access to the front spar car-
structure.
Thoroughly clean the forward and aft frames (webs) of the front spar carry-through
Figure 3-15 with solvent (18, Consumable Materials Chart, Section 2).
c.
Perform a´•visual
d.
Perform
a
inspection of
fluorescent
or
the cleaned
areas
structure in the
areas
shown
for evidence of cracks.
dye penetrant inspection
of the cleaned
area
per MIL-STD-6866 and
inspect
for evi-
dence of cracks.
If cracks are discovered, determine the crack size and method of repair as outlined in the WING FORWARD
SPAR CARRY-THROUGH STRUCTURE REPAIR/INSPECTION procedure.
e.
f.
If
no
cracks
are
noted, install the carry-through
cover
and the
pilot’s and copilot’s
seats.
WING FORWARD SPAR CARRY-THROUGH STRUCTURE INSPECTION
WITH REPAIR KIT
NOTE
The
areas
repaired
a.
Remove the
ry-through
b.
identified in
structure
pilot’s
by
and
Figure 3-15 should be inspected for cracking at
using the following inspection procedure:
the intervals
specified for
Chart 6
copilot’s
seats and the
carry-through
cover
to obtain access to the front spar
car-
structure.
Thoroughly clean the forward and aft frames (webs and reinforcing doubler) of the front spar carry-through
Figure 3-15 with solvent (13, Consumable Materials Chart, Section 2).
struc-
ture in the areas shown in
c.
Perform
a
visual
d.
Perform
a
fluorescent
inspection
or
of the cleaned
areas
for evidence of cracks.
dye penetrant inspection
of the cleaned
area
per MIL-STD-6866 and
inspect
for evi-
dence of cracks.
e.
If cracks
profile;
f.
3-28
If
are
discovered in the doubler
contact the Technical
no
cracks
are
or
the
Support Department
existing web face, the crack has progressed beyond the
at Raytheon Aircraft Company for further instructions.
noted, install the carry-through
cover
and the
pilot’s and copilot’s
doubler
seats.
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
g
INSPECTION
AREA
I´•,’"~
a
i
:C
008oo
i
;1
II
81"
,w
I
Ibl
,Rll
a
a
QQQ
I::
a
I I
"´•B,
BBg
00B
"Boe‘
g
INSPECTION-‘
BEND
RADIUS
O
AREA
AFT
WEB
FWD
INSPECT FOR CRACKS
AROUND HUCKBOLTS.
BETWEEN HUCKBOLTS,
AND ALONG THE RADIUS
OF THE CARRY-THROUGH
WEB IN THE INSPECTION AREAS.
LOCATIONS
INSPECTION
AREA
TYPICAL
CRACK
LOCATIONS
B
INSPECTION
AREA
ooO
o
’9\111
a
e
80
8
8
I,
8
QQ
a
I
i
a
TYPICAL
\\a\a´•
CRACK
LOCATIONS
a
a
_7
~s
oae
]
1
s
5
U~56
Ba
oo;
d;~O
D
~O
,1
(4
00
~aae
oo
aaooss
AREAINSPECTION
,oeeoa
8ggQ
pdB
sg
C94TC0382037
FORWARD
Wing
Fonnrard
Spar Carry-Through Structure Inspection
Figure
E18
WEB
3-15
3-29
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING FORWARD SPAR CARRY-THROUGH STRUCTURE REPAIR/INSPECTION
FIGURE 3- 15
NOTE
The extent of
repair/inspection is limited to cracking in the radius of the web
the web face around the fasteners in the lower front spar cap.
flange
and cracks in
BEND RADIUS CRACK
following procedure
The
should be
performed
to
repair/inspect cracks
in the bend radius:
A crack up to 2.25 inches in length must be stop drilled with a #30 drill bit at the crack ends, then inspected for
progression at each annual inspection or every 200 hours, whichever occurs first. One stop-drilled crack per left side
and one stop-drilled crack per right side of the bend radius is permissible, if neither one exceeds 2.25 inches.
a.
CAUTION I
I CAUTION
Caution must be used during the stop drilling operation. Do not drill into the spar cap, skin or any
other structure. A thin stainless steel sheet may be used to prevent damaging adjacent structure.
b.
A crack between 2.25 inches and 4.0 inches in
The
area
c.
must be
A crack
repaired
exceeding
length must be stop-drilled with a #30
flight hours with the applicable kit listed in
within the next 100
4.0 inches in
length
must be
drill bit at the crack ends.
Chart 7.
repaired priorto further flight with the applicable kit listed
in Chart
WEB FACE CRACK
The
following procedure
should be
performed
to
repair/inspect
cracks in the web face around the huck-bolt fasten-
ers:
A crack less than 1.0 inch in
shall be
length or one crack between two fasteners does not require immediate repair,
inspected for progression at each annual inspection or every 200 hours, whichever occurs first. A crack
anating
from
a.
one
fastener in two directions is considered to be
one
but
em-
crack.
CAUTION t
ICAUTION
Do not stop drill, due to the
One crack per left side and
b.
A crack
end shall be
c.
A crack
paired prior
3-30
more
one
crack per
than 1.0 inch in
repaired
possibility of damaging
right
structure behind web face.
side of the web face is
allowed, if neither
length or crack extending less than 0.5
flight hours with the applicable kit
within the next 25
passing through two fasteners and extending beyond
flight with the applicable kit listed in Chart 7.
for
inch
beyond
one
exceeds 1.0 inch.
the two fasteners
on
either
listed in Chart 7.
more
than 0.5 inch
on
either end shall be
re-
to further
E18
Ra~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
COMBINATION BEND RADIUS AND WEB FACE CRACKS
A combination of BEND RADIUS and WEB FACE CRACKS
cracks in both the forward and the aft web face
more
a.
If
than 1.0 inch
a
long
fuselage skin
skin doubler may be
instructions.
are
found, they
or
must be
acceptable
repaired prior to
crack is discovered around the
required.
are
in the bend radius
Contact the Technical
on
the
without
same
repair. However,
if there
are
any
airplane, or if any cracks
applicable kit listed in Chart 7.
side of the
further flight with the
opening for the lower forward carry-through fitting, an external
Support Department at Raytheon Aircraft Company for further
all cracks per the appropriate kit listed in Chart 7 if the limitations in the BEND RADIUS CRACK and
WEB FACE CRACK procedures are exceeded.
b.
Repair
c.
Install the
carry-through
cover
and the
pilot’s
and
copilot’s
seats.
CHART 5
INSPECTION PROGRAM FOR NON REPAIRED STRUCTURES
AIRCRAFT
INITIAL
FREQUENCY OF
SERIAL NO.
INSPECTION
INSPECTION
TC-1 THRU TC-2456
1,500 HOURS
500 HOURS
1,500 HOURS
1,500 HOURS
3,000 HOURS
500 HOURS
(EXCEPT TC-1471)
TE-1 THRU TE-1201
TH-1 THRU TH-1475
TH-1476 AND AFTER
500 HOURS
1,000 HOURS
CHART 6
INSPECTION PROGRAM FOR REPAIRED STRUCTURE
AIRCRAFT
INITIAL
FREQUENCY OF
SERIAL NO.
INSPECTION
INSPECTION
1,500 HOURS
1,500 HOURS
1,500 HOURS
1,500 HOURS
3,000 HOURS
1,500 HOURS
1,500 HOURS
1,500 HOURS
TC-1 THRU TC-2456
(EXCEPT TC-1471)
TE-1 THRU TE-1201
TH-1 THRU TH-1475
TH-1476 AND AFTER
E18
3-31
Raytheon Aircraft
SEECH BARON 55 AND 58 SHOP MANUAL
CHART 7
FRONT SPAR CARRY-THROUGH STRUCTURE REPAIR KITS
I
I
NUMBER
MODEL 55, SERIALS
1
58-4008-)S
TC-1 THRU TC-190;
I
AIRCRAFT
SERIAL NO.
MODEL A55, SERIALS
TC-191 THRU TC-501
(EXCEPT TC-350
AND
QUANTITY
KIT DESCRIPT\ON I
PART
I
PER AIRCRAFT
I
)FRONT
1 REQUIRED
SPAR
I
(STRUCTURE
CARRY-THROUGH
I
IREINFORCEMENT
((FORWARD FRAME)
TC-371);
MODEL S55, SERIALS
TC-371, TC-502 AND AFTER;
MODEL C55, SERIALS TE-1 THRU
TE-451; MODEL D55, SERIALS TE-452
THRU TE-767; MODEL E55, SERIALS
TE-768 AND AFTER
1
I
MODEL 55, SERIALS
TC-1 THRU TC-190;
MODEL A55, SERIALS
TC-191 THRU TC-501
(EXCEPT
TC-350 AND
58-4008-3S
1 FRONT SPAR
JCARRY-THROUGH
I
JSTRUCTURE
I
IREINFORCEMENT
REQUIRED
I
1
I
1 REQUIRED
I
i REQUIRED
I
1 REQUIRED
I
1 REQUIRED
((AFT FRAME)
TC-371);
MODEL 855, SERIALS TC-371, TC-502
AND AFTER; MODEL C55, SERIALS
TE-1 THRU TE-451; MODEL D55,
SERIALS TE-452 THRU TE-767;
MODEL E55, SERIALS TE-768 AND
AFTER
MODEL 58, SERIALS
TH-1 THRU TH-303,
1
58-4008-5S
I
1
FRONT SPAR
ICARRY-THROUGH
ISTRUCTURE
REINFORCEMENT
EXCEPT TH-255
(FORWARD FRAME)
MODEL 58, SERIALS
1
TH-1 THRU TH-303,
EXCEPT TH-255
I
(CARRY-THROUGH
I
ISTRUCTURE
REINFORCEMENT
58-4008-78
(FRONT
SPAR
(AFT FRAME)
MODEL 58, SERIALS TH-255, TH-304
AND AFTER
58-4008-9S
I
(FRONT SPAR
ICARRY-THROUGH
STRUCTURE
REINFORCEMENT
(FORWARD FRAME)
MODEL 58, SERIALS TH-255, TH-304
1
AND AFTER
I
58-4008-11S
1
FRONT SPAR
I CAR RY-TH RO UG H
STRUCTURE
REINFORCEMENT
(AFT FRAME)
3-32
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
SEATS
FRONT SEA T REI~IIO VAL
a.
Remove the seat stop
b.
Release the fore and aft adjustment lock.
c.
Move the seat aft until it clears the
or
stops
at the aft end of the seat tracks.
mounting
tracks.
FRONT SEA T INSTALLA TlON
a.
Align
the seat
installed in the
guide with the
same
location
b.
Pull up
on
and
ensure
that the seat is
c.
If the lock
guides
as
seat track. If shims
that from which
were
they
the fore and aft
pin
does not
installed in the front center seat
were
adjustment lever and slide the
securely in place.
align
with shims. Use shims
as
guide, they
should be
removed.
seat onto the seat track. Release the
adjustment
lever
with the holes in the center seat track, it will be necessary to reposition the seat
needed to center the locking pin with the holes in the seat track.
NOTE
Shims (three inches long X 0.3 inch
as shown in Figure 3-16. The shims
as
d.
Pull up
that the
e.
E18
shown in
on
Figure
wide) may be fabricated from 0.016 6061 T6 sheet aluminum
placed inside the seat guide and formed around the guide
are
3-16.
the fore and aft
locking pin
has
adjustment lever and slide the seat through the full
positive engagement in all holes of the seat track.
travel of seat
adjustment.
Ensure
Install the seat stops at the aft end of the seat tracks.
3-33
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
SHIMS
MAKE
FROM
.016
bObl-Tb
SEAT
GUIDE
ALUMINUM
_L
.3
INCH
I
_~
i~----,
CENTER
SEAT
TRACK
CENTER FRONT
VIEW FROM
SHTM
SEAT LEG
FRONT
Seat Track Shim Installation
Figure
3-16
CENTER SEA T RN~10 VAL
a.
Release the fore and aft
b.
Remove the seat stop from the aft end of the center track.
c.
Release the fore and aft adjustment and
adjustment
lock and
move
move
the seat forward
against the stop.
the seat aft until it clears the
mounting
tracks.
NOTE
If the
rear
facing
TH-764, the
carry-
seats
are
to be
two MS24694S51
through
changed
screws
structure are to be
that
replaced
to forward
facing seats on aircraft serials TH-733 to
the center seat center tracks and the rear spar
with NAS1203-5 screws. The MS24694S51 screws are
secure
to be discarded. The center seat center track screws
only need to be replaced one time unless an
inspection reveals a broken screw or stripped threads. An entry is to be made in the Maintenance
Log that the CENTER SEAT CENTER TRACK SCREWS HAVE BEEN REPLACED.
CENTER SEA T INSTALLA TION
Place the seat in
a.
position
and
align
the seat
guides
with the
b.
mounting
Release the fore and aft adjustment lock and slide the seat onto the
lock and make certain the seat is securely in place.
c.
Replace
3-34
the seat stop
on
track.
mounting
track.
Engage
the fore and aft
the aft end of the center track.
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
FIFTH AND SIXTH SEA T REMOVAL
a.
Raise the seat bottom up to release the tension
b.
Remove the seat back support rod from the
c.
Remove the
on
the seat back support rod.
mounting brackets
and fold the seat back forward.
bolts and seat.
attaching
FIFTH AND SIXTH SEA T INSTALLA TION
in
place
with
attaching
bolts.
a.
Position the seat and
b.
Raise the seat bottom and insert the seat back support rod into the
secure
mounting
brackets.
FIFTH AND SIXTH SEA T STOWAGE
The fifth and sixth seat may be folded either in
This may be accomplished as follows:
horizontal
a
or
vertical
position
to
provide additional
cargo space.
VERTICAL POSITION
vertical
a.
Fold the seat bottom up to
b.
Fold the seat support into the retract
c.
Position the seat
against
a
the
rear
position.
position.
bulkhead in
a
vertical
position.
HORIZONTAL POSITION
a.
Fold the seat support into the retract
b.
Fold the seat back forward and
position
position
it
on
and
position
top of the
the seat bottom
on
the floorboard.
seat bottom.
SEA T-BA CK ADJUS TMEN T
pilot’s seat-back adjustment is a three-position mechanical stop. The copilot’s and
passenger’s seat-back adjustments are controlled by either a three-position mechanical stop or a Roton lock. On
serials TC-2258 and after, TE-I 164 and after, TH-1027, TH-1062, TH-1080 and after, the Roton locks were replaced
with Hydroloks. On airplanes equipped with vertically adjusting copilot’s seats, the copilot’s seat-back adjustment is
controlled by the three-position mechanical stop. The lever for actuating the Roton lock or Hydrolok adjusters is on
the side of the seat toward the front, while the lever for the mechanical adjusters is at the base of the seat back.
Roton lock and Hydrolok servicing information may be found in Section 2.
The device used to control the
VERTICAL ADJUSTING SEA TS
FIGURE 3-17
Airplanes with serials TH-1389, TH-1396 and after are equipped with vertically adjusting seats for the pilot (copilot’s
seat is optional). The seat is raised and lowered by a gas spring mounted underneath the seat. The seat is adjustable through a range of 1.3 inches for improved visibility and crew comfort. The raising and lowering action is initiated by pulling up on the release lever located on the front RH side of the seat. When the release lever is raised,
two ratchet-type cam lots are disengaged from sector gears attached to the gas springs mounted on each side underneath the seat, allowing the gas spring’s piston rod to extend retract, raise or lower the seat. To raise the seat,
must be shifted forward. To lower the seat, the
the
pilot’s weight
gas
spring tension.
E18
weight
must be shifted to the
rear
to overcome the
3-35
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
I
~EAR
GAS SPRING
~ll(d
RELEASE
LEVER
ACTVATOR
ROD
--1
ioO
TORQUE
TUBE
ADJUSTING
LEVER
3631351
Vertically Adjusting
Figure
3-36
Seat
3-17
E18
RayC~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
GLARE SHIELD REMOVAL
(ALL TC, TE,
AND TH SERIALS EXCEPT TH- 1389, TH- 1396 AND
AFTER)
attaching
Remove the
b.
Pull the
glare
c.
Pull up
gently
d.
Disconnect the
wiring for the
e.
Disconnect the
glare
f.
Disconnect the defroster duct tube from the main defroster at the
g.
Remove the
screws on
both sides of the
shield.
a.
shield away from the slide-on fasteners located in three
on
the
glare
a.
places
at the base of the windshield.
shield.
compass and
shield air
floodlights
conditioning
at the connectors.
duct from the main duct at the
clamp.
clamp.
glare shield from the airplane.
GLARE SHIELD INSTALLA TION
AND
glare
(ALL TC, TE,
AND TH SERIALS EXCEPT TH- 1339 TH- 1396
AFTER)
Place the
glare shield
in the
and connect the electrical
airplane
wiring for the compass and
the
floodlights
at the
connectors.
b.
Connect the defroster duct and the air
c.
Place the
glare
shield down in
conditioning
position making
sure
ducts and
that it fits
secure
them with
clamps.
properly over the fasteners
at the base of the wind-
shield.
d.
Secure the
glare shield
both sides with the attach
on
GLARE SHIELD REMOVAL
(TH-1389,
screws.
TH- 1396 AND
AFTER)
At serials TH-1389, TH-1396 and after, the glare shield is a two-part assembly. The forward section must be removed before the aft section is removed. The words "forward" and "aft" are used to indicate position in relation to
the
airplane.
Remove the
glare
shield
as
a.
Remove the five
b.
Lift out the forward section of the
c.
Remove the three
d.
Remove the
e.
Locate and disconnect the compass
f.
Remove the aft section of the
screws
which pass
screws
screws on
through
glare
which pass
glare
a.
Place the aft section of the
b.
Connectthe electrical connector.
c.
Install the
d.
Install the three
E18
glare
glare
shield into the instrument
panel.
through
the aft section of the
glare
shield into the instrument
panel.
glare shield.
light,
annunciator
lights,
and flood
light
connector.
shield.
(TH-1369,
TW- 1396 AND
AFTER)
shield into the proper location.
each side of the
screws
the forward section of the
shield.
each side of the
GLARE SHIELD INSTALLA TION
screw on
follows:
which pass
glare shield.
through
the
glare
shield into the instrument
panel.
3-37
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
e.
Place the forward section of the
f.
Install the five
screws
glare shield into its
which pass
through
the
proper location.
glare shield
into the instrument
panel.
HEADLINER REMOVAL (TH-1027, TH-1062, TH-1067, TH- 1080 AND
a.
Remove the seats from the
b.
Remove the
webbing
webbing
flight compartment
as
and hat shelf from the aft
AFTER)
outlined in FRONT SEAT REMOVAL in this
baggage compartment
and then
remove
the
chapter.
clips retaining
the
and hat shelf.
Remove the snap-on cover over the rear shoulder harness inertial reel and remove the
c.
mounting bolt that attaches the inertial reel to the airplane. Pull the upholstery inserts from the
the
RH
on
and LH side of the
molding
airplane and remove the molding attach screws.
d.
Remove the
e.
Remove the lower aft bulkhead closure. The closure is held in
f.
Remove the tape (42, Consumable Materials Chart, Section
where the overhead air ducts join.
screws
attaching
the aft garment
hanger to
the
airplane
and
remove
the
hanger.
place by velcro, fasteners.
2) (working through
the aft bulkhead
closure)
at the
seam
g.
Remove the
h.
Remove the attach
screws
securing
the
i.
Remove the attach
screws
securing
the trim above the
j.
Remove the coat hooks
inserts
are
glare
shield
as
outlined in this
chapter
molding
under GLARE SHIELD REMOVAL.
around the windshield and
flight compartment
remove
door and
the
remove
Remove the attach
move
the
molding
screws
from the
from the
molding
around the windows
on
remove
the RH and LH side of the
screws attaching the overhead forward console to the headliner and
pull down
the console forward to disconnect the console air duct and the main air duct.
on
the
The
mounting
airplane.
Re-
the console while
n.
Disconnect the
o.
Remove the console from the
p.
Gently pull down on the headliner to disconnect
the length of the headliner.
it from the velcro fasteners. The velcro tape is
q.
Disconnect the electrical wiring to the headliner
lights.
r.
Remove the headliner through the
wiring
molding.
airplane.
Remove the
m.
pulling
the trim.
on the upper window molding, then pull the
upholstery inserts from the
located between and below the passenger compartment windows.
k.
Pull the snap-on covers from the pilot’s and copilot’s shoulder harness inertial reels and
bolt that attaches the reel to the airplane. Remove the reel from the
airplane.
i.
molding.
from the console and tag and
identify the wiring.
airplane.
spaced evenly
across
HEADLINER INSTALLA TION
a.
Place the headliner in the
b.
Place the headliner in
press
3-38
on
the
areas
flight compartment
(TN- 1027
airplane
A connector is located above the
door
or
utility
door.
TH- 1062, TH- 1067 TH- 1080 AND
and connect the electrical
position (ensuring
the aft
pilot’s window.
AFTER)
wiring.
that the aft headliner air duct and the aft main air duct fit
properly)
and
where the velcro tape is located.
E18
Ray~hean Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
to the forward overhead console at the connector.
c.
Connect the electrical
d.
Place the forward overhead console into
Seal the air duct
seam
with sealant
e.
Secure the console in
f.
Replace
the
wiring
molding
(43,
position, making
with the attach
place
around the windows
correctly
that the air ducts slide
sure
Consumable Materials Chart, Section
into
position.
2).
screws.
the RH and LH side of the
on
airplane
and
secure
with the attach
screws.
Replace the upholstery inserts (located between the passenger compartment windows,
compartment windows, and in the aft baggage compartment).
g.
with attach
below the passenger
h.
Replace
the forward and aft coat hooks and
i.
Replace
the trim above the
j.
Install the
molding
k.
Install the
glare
i.
Wrap tape (42, Consumable Materials Chart, Section 2) (working through the aft bulkhead closure) around the
seam
secure
flight compartment
around the windshield and
shield
as
door and
n.
Install the aft garment hanger in the airplane and
o.
install the RH and LH
rear
screws.
screws.
chapter.
join.
Install the aft bulkhead closure that is held in
p.
with the attach
outlined in GLARE SHIELD INSTALLATION in this
where the aft overhead air ducts
covers over
secure
with the attach
secure
m.
ping
screws.
place
with velcro fasteners.
secure
with attach
shoulder harness inertial reels and
screws.
secure
with attach bolts, then
replace the snap-
the inertial reels.
Install the mounting
clips
baggage webbing
for the
and hat
shelf, then
mount the hat shelf and
baggage web-
bing.
Install the RH and LH forward shoulder harness inertial reels and
q.
the snapping covers over the inertial reels.
Install the
flight compartment
seats
as
secure
them with the attach bolts, then
outlined in FRONT SEAT INSTALLATION in this
replace
chapter.
CABIN DOOR
CABIN DOOR REMOVAL AND INSTALLATION
FIGURES 3-18 AND 3-19
a.
Remove the inboard door handle,
ashtray assembly
and the
arm
rest.
NOTE
The
attaching
screws
screws
for the
arm
for the
rest
are
ashtray assembly are
located behind two
car
upholstery panel.
b.
Remove the
attaching
screws
from the center
c.
Remove the
attaching
screws
and release the snaps
d.
Remove the lower
818
located behind the ash tray insert, and attaching
plugs in the inboard side of the arm rest.
on
Lift the
the lower
panel
up and out.
upholstery panel.
upholstery panel.
3-39
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
e.
Remove the
f.
With the door open, insert a screwdriver between the doorstop and the bottom of the door.
applying a downward pressure on the doorstop until the stop is released from the door
screws
from each
hinge
cover
(see Figure 3-18).
while
g.
Remove the
attaching
bolts from each door
Slowly close the door
(see Figure 3-19).
hinge (see Figure 3-18).
NOTE
Shims have been installed between the hinges and the door to obtain a proper fit. The shims should
be retained and the same number of shims installed under each hinge when the door is installed.
h.
Installation is
accomplished
in the
reverse
of the removal
procedure.
ATTACHING BOLT
H~NGE:
SHIM
Mjs
HINGE COVER
PHILLIPS SCREWS
Cabin Door
Figure
Hinge
3-18
i!
Cabin Door
Figure
3-40
Stop
3-19
E18
NaylfNeon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
CABIN DOOR LA TCHING ADJUSTII´•IENT
If any of the
following
conditions exist, check and
adjust
the cabin door
latching
mechanism:
The door is difficult to close.
There is excessive wind noise around the door.
The door is not
The door is
opening
The door has
a.
airtight
in
recently
or
watertight.
flight.
been removed
or
repaired.
Ensure that the door’s internal latch mechanism is not
With the door in the open position, operate the
mechanism is operating smoothly and properly.
i.
binding and/or preventing
proper door
latching mechanism several times to
closing
ensure
as
follows:
that the internal
With the door still in the open position, rotate the inside door handle counterclockwise as far as possible.
2.
Mark the inside handle escutcheon plate at the edge of the blade protruding from the inner forward end of the handle.
Place the latch in the open position and then close and latch the door. Check to see that the handle rotates
position that was marked in the previous step. If the handle does not line up with the mark, open the door and
remove the door upholstery. Inspect the latching mechanism to determine the reason for the interference and make
3.
to the
the necessary
adjustments.
NOTE
The
areas
possible interference
of
are
where the lower
pin,
the upper latch hook, and the aft latch
bolt engage in the door frame.
b.
The latches may
1.
require adjustment
UPPER LATCH
There
are
to ensure
three
points
positive
door
that should be
locking
as
inspected
follows:
and/or adjusted
on
the upper latch.
(Sheet I of 3), check to ensure that the upper latch mechanism is over center
accomplished by using a small inspection mirror to see that the upper operand the forward edge of the upper operating link is forward of the forward
the
link
is
screw
adjustment
against
ating
mechanism is not over center when the door is latched, adjust the over
If
link.
the
latch
of
the
lower
operating
edge
a)
Referring
to
Figure
when the door is latched. This
center
stop
b)
3-20
can
be
screw.
Referring to Figure 3-20 (Sheet 1 of 3), check to ensure that the upper latch hook pin is positioned so
touching the aft portion of the hook without riding on the hook. If the upper hook does not properly
pin, move the pin forward or aft, tit has four positions) to obtain proper adjustment.
that it is almost
engage the
Check for proper adjustment of the door upper latch bracket in the door sill above the door. If the door
does not fit properly in the frame (inboard/outboard) when closed and latched, leaving a noticeable gap between the
door and the frame, the upper latch bracket needs to be adjusted "in" to create more tension on the door. This can
c)
be
accomplished by adjusting
E18
the forward tension
screw.
Refer to
Figure
3-20
(Sheet
1 of
3).
3-41
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
2.
LOWER LATCH
The lower aft latch
pin
should be
adjusted in the latched (closed) position so that the
through both the striker plate and the door opening frame
to a minimum of 0.05 inch below the lower surface of the door opening frame, as shown in Figure 3-20 (Sheet 2 of
3j. Adjust the pin as follows, so that it just clears the striker plate when the latch is in the unlatched (open) position,
and does not interfere with door opening.
shoulder
(straight sided) portion
of the
pin
has extended
NOTE
The amount of the
pin protruding from
the door with.the latch open will
the bottom of the door and the door frame in the
a)
Remove the
b)
Turn the barrel to extend
safety wire
depend
on
the gap between
fuselage.
in the turnbuckle.
or
retract the
pin
as
necessary.
NOTE
It may be necessary to shorten the
pin guide as shown in Figure 3-20
pin guide by grinding a maximum of 0.2 inch off the top of the
(Sheet 2 of 3), in order to obtain enough travel to make this
adjustment.
c)
3.
Safety
the turnbuckle.
AFT LATCH BOLT
Check to
ensure
that the aft latch bolt
et on the aft door frame as far as
ferring
to
Figure
3-20
(Sheet
3
possible without bottoming
of 3).
provides a pre catch and protrudes into the sockadjustment is required, proceed as follows, re-
out. If
a)
Disconnect the
b)
Disconnect the lower aft latch pin mechanism from the
c)
Rotate the tube to allow the bolt to protrude the proper distance.
operating
tube at the inside door handle.
operating
tube.
NOTE
When this is done the outside handle may protrude up to 0.25 inch into the airstream, which is
ac-
ceptable.
d)
Connect the lower aft latch pin mechanism to the
operating
tube. Connect the
operating
tube to the in-
side door handle.
NOTE
The aft latch bolt
can
be
aft side of the door and
four
c.
the
the
screws.
Install any
3-42
adjusted inboard or outboard by loosening the four retaining screws on
moving the bolt inboard or outboard as necessary, and then tightening
upholstery
and/or
equipment
that
was
removed.
E18
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
A
A
1
1
WARNING
VERIFY DOOR IS PROPERLY
LATCHED BEFORE TAKEOFF
VIEW LOOKING OUT
AT RH SIDE OF CAB
C
j
DOOR
UPPER
HOOK
LATCH
FORWARD
r’
DOOR UPPER
LATCH BRACKET
FWD
TENSION
SCREW
UPPER LATCH HOOK PIN SHOULD
TOUCHING THE AFT PORTION OF
WITHOUT RIDING ON IT.
BE ALMOST
THE HOOK
e~
O
OVERCENTER
UPPER
OPERATING
O
LOWER
OPERATING
ADJUSTABLE
STOP
SCREW
LINK
WHEN DOOR IS LATCHED. THE FORWARD EDGE
OF IHE UPPER OPERATING LINK SHOULD BE
AGAINST THE OVERCENTER ADJUSTABLE STOP
SCREW AND FORWARD OF THE FORWARD EDGE
OF THE LOWER OPERATING LINK.
LINK
VIEW
LOOKING
VIEW
A-A
FROM
C9101555
ABOVE
ROTATED
180"
Cabin Door Latch Points
Figure
E18
3-20
(Sheet
1 of
3)
3-43
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
TURNBUCKLE
WIRE
CUTOUT
PIN
STRIKER
LOWER
AFT
IN
DOOR
PAN
GUIDE
PLATE
LATCH
PIN
AFT
VIEW
CLEVIS
LOOKING
GRIND OFF TOP
REQUIRED TO A
\1
CUTOUT
TRIKER
PLATE
IN
OUTBOARD
OF PIN GUIDE.
IF
MAXIMUM OF 0.2 INCH
DOOR
PAN
DOOR OPENING
FRAME
PIN,
GUIDE
i;;
q
VIEW
s
PIN
.05 INCH MINIMUM ENGAGEMENT
ABOVE TAPERED AREA OF THE PIN
IS REQUIRED
D
C91001556
Cabin Door Latch Points
Figure
3-44
3-20
(Sheet
2 of
3)
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ROTATE THE OPERATING TUBE
TO ADJUST BOLT PROTRUSION
ADJUST LATCH BOLT
8Y LOOSENING
THESE SCREWS (4]
BOLT
OPERATING
TUBE
VIEW
INSIDE
DOOR
C
LOOKING
OUTBOARD
Cabin Door Latch Points
Figure
UTILITY BAGGAGE DOOR
3-20
(Sheet
3 of
3)
(OPTIONAL)
The
utility baggage compartment door is located on the right hand side of the fuselage, aft of the wing, below the
window. The door is opened by turning a "D" shaped handle and is held in the open position by a support rod
in the upper right hand corner. A small stop chain prevents the door from being opened too far and striking the trailing
edge of the flap. The latching mechanism incorporates a bayonet type latching mechanism. When the mechanism
is actuated (by turning the handle) the bayonet points enter the door facing and hold the door securely in the closed
position. A locking mechanism, actuated by a key from outside the airplane, prevents the handle from turning.
rear
UTILITY BAGGAGE DOOR REMO VAL AND INSTALLA TION
NOTE
Parts that rotate, swivel
or
slide
(metal
to
metal)
and that have
brication, should be lubricated with SAE 20W oil, 1 OW30 oil
Chart, Section 2).
or
a.
Open
b.
Disconnect the stop chain at the upper
c.
Remove the piano hinge wire at the right hand side of the door and
reverse of the removal procedure.
the door to the full open
no provisions or instructions for luequivalent (5, Consumable Materials
position.
right
hand
corner
of the door.
remove
the door. Installation of the
baggage
door is the
UTILITY BAGGAGE DOOR RIGGING
FIGURE 3-2 1
a.
Removethe door.
b.
For
E18
ease
of maintenance, place the door
on a
bench.
3-45
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
Remove the upholstery panel and turn the handle to the closed position and note that the vertical legs on the
latching mechanism "T" bracket of the door travels 20" 10" past the center position with a slight retraction of all
three bayonet points. In this position (20"
10" past center) the latching mechanism "T" bracket should fully engage
the stop and the "D" handle should be in a horizontal position.
c.
d.
If the vertical
of the stop,
legs of the latching mechanism "T" bracket do not travel 20" -t- 10" past center with full engagement
adjust the length of the bayonet post or the position of the stop until this reading is attained.
After the proper alignment, lubricate all moving parts of the latching system with a mixture of oil (16, Consumable
Materials Chart, Section 2), and graphite (27, Consumable Materials Chart, Section 2). Apply door-ez to the bayonet
attach points in the area of the striker plates and guide blocks.
e.
f.
After
lubricating
the
designated
torque should be required
g.
Install the interior
areas, actuate the handle several times. A maximum
to actuate the door handle to the closed and latched
upholstery panel
and install the door
on
the
pull
of 40
inch-pounds
of
position.
airplane.
AFT BA GGA GE DOOR
The aft
baggage door is located on the right hand side of the fuselage just aft of the trailing edge of the wing. The
opened by pushing in the latch button which releases the locking mechanism and allows the door to open.
door may be locked by the key furnished with the airplane.
door is
The
AFT BA GGA GE DOOR REMO VAL AND INSTALLA TION
NOTE
Parts that rotate, swivel or slide (metal to metal) that have no provisions or instructions for lubrication should be lubricated with SAE 20W oil, 10W30 oil or equivalent (5, Consumable Materials
Chart, Section 2).
the door to the full open
a.
Open
b.
Remove the
c.
Remove the door from the
d.
Installation of the aft
piano wire hinge
position.
at the
edge
of the door.
airplane.
baggage
door is the
reverse
of the removal
procedure.
AFT BA GGA GE DOOR A DJUS TIMENT
Adjustment of the door is accomplished by readjusting the position of
rear edge of the door frame. Turn the attach screws on the striker plate
obtain the desired holding tension of the door in the closed position.
3-46
the
and
latching mechanism striker plate at the
move the striker plate either in or out to
618
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
J
ADJUSTMENT POINT
Lc-´•-----~
4ZBBP
j
LOCKING BAR
20"
t
O
100
LATCHING MECHANISM "T" BRACKET
STO
BAYONET POINT
TH038
LATCHING MECHANISM
Utility Door
Figure 3-21
E18
3-47
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
INTERIOR DOOR HANDLE
INTERIOR DOOR HANDLE REMOVAL AND INSTALLA TION
NOTE
It may be necessary to place the door handle in the unlatched
the door handle.
position
to access both screws that
secure
a.
Remove the two
screws
that
secure
the interior door handle base
b.
Slide the interior door handle from the shaft,
to the shaft. Refer to Figure 3-22.
c.
Rotate the door handle 90" clockwise,
maintaining
maintaining
the
the base
plate.
same
plate
orientation of the door handle with respect
in the
same
position
as
shown in
Figure
3-22.
NOTE
Interior door handle
configuration
d.
Slide the interior door handle
e.
Latch the door
by rotating
over
of
some
airplanes
the shaft and secure,
may differ from that shown in
using
the
screws
Figure
removed in step
3-22.
a.
the interior door handle counterclockwise.
CAUTION i
Ic~unon
Rotation of the interior door handle without
result in
unlatching
depressing
the handle lock release button should not
of the door.
f.
Rotate the interior door handle clockwise without depressing the handle lock release button. If the door remains
latched, proceed to step g. If the door becomes unlatched, repeat steps a through e.
g. With the door
should unlatch.
3-48
latched, depress the handle lock release button while rotating the door handle clockwise. The door
818
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
STEP
CORRECT
INSTALLATION
INCORRECT
INSTALLATION
BASE
PI AIE
UP
FREE-PLAY*
X
,-t~r
u’
STEP
DEIAII
A
7
FWD
FWD
FREE-PLAY+
A
FORWARD
DOOR
EDGE
NOTE:
FREE-PLAY TRAVEL OF THE COPILOT’S
DOOR HANDLE WHEN IN LATCHED POSITION
FORWARD
DOOR
EDGE
COPILOT’S
CORRECT
INSTALLATION
I/
DOOR
HANDLE
INCORRECT
INSTALLATION
AFT
DOOR
EDGE
/I
ii
AFT
DOOR
EDGE
VP
ii
I
UP
BASE
PLATE
STEP
FWD
II
AFT
Is
DEIAIL
FREE-PLAY*
B
8
NOTE:
FREE-PLAY TRAVEL OF THE
UTILITY DOOR HANDLE WHEN
IN LATCHED POSITION
UTILITY
DOOR
HANDLE
FREE-PLAY+
TH528
992572AA
Interior Crew Door Handle and Interior Utility Door Handle Installation and Orientation
Figure
E18
3-22
3-49
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
CARGO DOOR (TH-1 AND AFTER)
DOOR REMOVAL AND INSTALLA TION
NOTE
Parts that rotate, swivel or slide (metal to metal) that have no
tion should be lubricated with SAE 20W oil, 10W30 oil or
provisions or instructions for lubricaequivalent (5, Consumable Materials
Chart, Section 2).
a.
With the doors open,
b.
Support the
c.
Installation of the doors may be accomplished by
remove
doors and
the
Phillips
the
remove
head
screws
that attach the scissors door stop to the door sill.
hinge pins by pulling straight
reversing
up.
the removal
procedures.
DOOR ADJUSTMENT
If the cargo door does not close properly or permits air leaks while
completely closed, several adjustments may be
made to assure proper sealing of the door. After
determining the origin of the air leakage as to whether it is from
around the forward half of the cargo door or the aft half of the door, make the
following adjustments as necessary:
ADJUSTMENT OF THE AFT HALF OF THE DOOR
Adjustments of the aft door may be performed by removing
ening the door latch connecting tube assembly.
a.
the
upholstery paneling
and
shortening
or
length-
NOTE
By shortening
b.
To
the
adjust the length
"IN" to shorten the tube
connecting
tube assemblies, the door will be
pulled tighter against
the door seal.
of the
connecting tube assembly, remove the cotter key, washers and pin.
assembly and turn the pin eye "OUT"’ to lengthen the tube assembly.
c.
After the desired
d.
Replacethe upholstery paneling.
length
has been set, install the
pin,
washers and cotter
Turn the
pin eye
key.
ADJUSTMENT OF THE FORWARD HALF OF THE DOOR
If the air leakage is around the forward half of the door, the
necessary
latch striker plate located in the center of the rear door.
a.
b.
For
a
tighter fit, loosen
the two
Phillips
head
screws
and
move
adjustments
the striker
may be made at the door
plate inboard.
DOOR LATCH PIN ADJUSTMENT
If the forward door does not open
freely,
the door latch
by the following adjustments:
a.
Removethe
b.
Remove the cotter
c.
Loosen the
lengthen
3-50
pins may
not be
retracting enough.
This may be corrected
upholsterypaneling.
keys, pins
and washers.
pin eye jam nut and turn the pin eye "IN" to shorten the tube assemblies; turn the
the tube assemblies.
pin
eye "OUT" to
E18
Rayl~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
d.
After the desired
e.
Replace
the
length
has been set,
tighten
the
pin
eye
jam
nut. Install the
pins,
washers and cotter
keys.
upholstery paneling.
FORWARD BAGGAGE AND A VIONICS COMPARTMENT DOOR
baggage compartment door is located on the right hand side of the nose area. Some doors are opened
the two
by depressing the two latch buttons located at the base of the door and some doors are opened by turning
has a
also
door
The
rod.
the
in
a
held
is
door
The
location.
support
Dzus fasteners at the same
open position by
the
from´•outside
actuated
is
a
airplane.
by key
locking mechanism which
The forward
FORWARD BAGGAGE DOOR REMOVAL AND INSTALLATION
NOTE
Parts that rotate, swivel
or
slide
(metal
to
metal)
that have
tion should be lubricated with SAE 20W oil, 10W30 oil
no
provisions
or
instructions for lubrica-
equivalent (5, Consumable Materials
or
Chart, Section 2).
position.
the door to the full open
a.
Open
b.
Disconnect the door
c.
Installation of the forward
hinges
at the
top of the door and
baggage door
is the
remove
reverse
the door from the
of the removal
airplane.
procedure.
ADJUSTMENT OF THE FORWARD BAGGAGE DOOR
the
Adjustment of the door is accomplished by readjusting the position of the latching mechanism striker plates at
bottom edge of the door frame. Adjustment is accomplished by turning the attach screws on the striker plates and
moving the striker plates either in or out to obtain the desired holding tension of the door in the closed position.
WINDOWS
WINDSHIELD REMOVAL
(ONE AND
TWO
PIECE)
FIGURE 3-23
a.
Remove the
glare shield
b.
Remove the
attaching
c.
Remove the
screws
and after, hook and
pile
and outside air temperature gage
screws
from the defroster duct and
and spacers from the
tape is used.
strips
(if installed).
move
duct to clear lower
row
of rivets
on
windshield.
On TE-832 and after, TH-104 and after, TC-502
glare shield angles.
from around the inside of the windshield.
d.
Remove the trim
e.
To facilitate installation, mark the location of the trim
f.
Remove the rivets from around the windshield.
g.
Remove the windshield. The
one
piece
strip clips.
windshield is removed
by moving
it to the left.
NOTE
Due to the windshield
being sealed, considerable effort
may be
required
to break the windshield
loose from the canopy section.
E18
3-51
Ray~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
DEFROsTER DUCT
ATTACHING
LD
ANGLE
DEFROSTER
DUCT
LARESHIE LD
CLARESHIE LD
ANGLE ATTACHING
SCREW
/WINDSHIELD
GLARESHIELD
ANGLE
Windshield
Figure
FRAME
TH038
s41752nn
(Typical)
3-23
WINDSHIELD INSTALLATION
a.
Clean the sealer from the
canopy section where the old windshield
b.
Trim the
tooling
tabs from the windshield. Place the windshield in
was
removed
using toluol.
position and mark the areas where material
top first to maintain edge distance for side
must be removed from the windshield to obtain a
proper fit. Trim from the
rivets.
c.
Remove the windshield and trim off
d.
Place the windshield in position and cleco in
place
e.
Back drill the windshield frame
f.
2)
excess
using
the
material
existing
as
using
Place the windshield in
h.
Using AN470AD4 rivets,
position
secure
and cleco in
the
pilot
holes provided.
holes in the canopy section
Remove the windshield, clean and deburr all holes and
to the windshield frame where it makes contact with the
g.
determined in step b.
as a
guide.
apply sealer (43, Consumable Materials Chart, Section
canopy section.
place.
the windshield to the
canopy section.
NOTE
i.
When
riveting
step
of the windshield removal procedure.
e
Secure the
glare
the windshield in
shield
angles
in
after, TC-502 and after tape is used.
j.
Position the defroster duct and
place, install the trim strip clips
place with attaching
secure
in
place
in the
same
locations
as
screws, nuts and spacers. TE-832 and
with the
attaching
marked in
after, TH-104 and
screws.
3-52
E18
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
k.
Install the trim
i.
Install the
m.
Clean and
strips.
glare
shield and outside air temperature gage
paint
as
(if removed).
necessary.
STORM WINDOW REMOVAL AND INSTALLATION
a.
Remove the
attaching bolt from the
b.
Removethe
hingepin.
c.
Installation is
storm window sleeve
accomplished by reversing
the above
assembly.
procedure.
STORM WINDSHIELD REMOVAL AND INSTALLATION
(TE-768 AND AFTER; TH-I AND AFTER)
a.
Remove the two
b.
Installation is
internally threaded hinge pins.
accomplished by reversing
the above
FORWARD LH WINDOW REMOVAL
(TE-768 AND AFTER;
required to gain
a.
Remove the
b.
Remove the trim
c.
Remove the rivets from around the window.
d.
Remove the window.
upholstery panels
as
strip from around the inside
access
AFTER)
to the window frame.
(TE-768 AND AFTER;
Clean the searer from the canopy section where the old window
Materials Chart, Section
TH-I AND
of the window.
FORWARD LH WINDOW INSTALLA TION
a.
procedure.
was
TH-l AND
removed
using
AFTER)
toluol
(20, Consumable
2).
Place the window in
c.
Remove the window and trim off the
d.
Place the window in
e.
Back drill the window frame,
f.
Remove the window; clean and deburr all holes and apply sealer (4, Sealing Chart, Section
1/2 inch wide on the canopy section where the old sealer was removed.
position
position
and mark the
where material must be removed to obtain
b.
excess
and cleco in
using
area
the
material
as
place, using
existing
a
proper fit.
determined in step b and check for proper fit.
the
pilot holes provided.
holes in the canopy section
as a
guide.
2)
to
an area
ap-
proximately
position
g.
Place the window in
h.
Using
i.
rnstall the trim
j.
Install the storm window.
E18
AN470AD4 rivets,
and cleco in
secure
place.
the window to the canopy section.
strip.
3-53
Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
FORWARD LH WINDOW REMOVAL
a.
Remove the storm window.
b.
Remove the
c.
Remove the trim
d.
Remove the
e.
To facilitate installation, mark the location of the trim
f.
Remove the rivets from around the window.
g.
Remove the window.
upholstery panels
strip
screws
as
required
to
gain
access to
the window frame.
from around the inside of the window.
and nuts
attaching
the storm window striker to the window frame.
strip clips.
FORWARD LH WINDOW INSTALLA TION
a.
Clean the sealer from the canopy section where the old window
was
Materials Chart, Section
2).
b.
Place the window in
position
c.
Remove the window and trim off the
d.
Place the window in
e.
Back drill the window frame
f.
Remove the window, clean and deburr all holes and apply sealer
on the canopy section where the old sealer
position
Place the window in
excess
and cleco in
using
h.
Using
position
AN470AD4 rivets,
using
toluol (20, Consumable
and mark the areas where material must be removed to obtain
the
material
as
secure
proper fit.
place using the pilot holes provided.
existing
and cleco in
a
determined in step b.
holes in the canopy section
proximately 1/2 inch wide
g.
removed
as a
guide.
(4, Sealing Chart, Section 2)
was
to
an area
ap-
removed.
place.
the window to the canopy section.
NOTE
When
e
riveting the window
of the window removal
in place, install the trim strip clips in the same locations
procedure.
i.
Install the trim
j.
Attach the storm window striker to the window frame.
k.
Install the storm window.
i.
Clean and paint
m.
Install the
3-54
as
marked in step
strips.
as
necessary.
upholstery panels.
E18
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
CABIN DOOR WINDOW REMOVAL
a.
Remove the inboard door handle, ash tray and
b.
Remove the center
c.
Remove the trim
d.
To facilitate installation, mark the location of the trim
e.
Remove the rivets around the window.
f.
Remove the window.
arm
rest.
upholstery panel.
strip
around the inside of the window.
strip clips.
CABIN DOOR WINDOW INSTALLATION
a.
Clean the sealer from the door where the old window
was
removed
using
toluol
(20, Consumable
Materials
Chart, Section 2).
b.
Place the window in
c.
Remove the window and trim off
d.
Place the window in
position
position
and mark the
excess
areas
material
and cleco in
where material must be removed to obtain
as
a
proper fit.
determined in step b.
place using the
two
pilot holes
on
the aft side of the window frame.
NOTE
To eliminate the
drilling
the
possibility of the door being warped, the door
attaching holes and riveting the window in place.
must be closed and latched when
e.
Back drill the window frame
f.
Remove the window, clean and deburr all holes and apply sealer (4, Sealing Chart, Section
1/2 inch wide on the door where the old sealer was removed.
using
the
existing
holes in the door
as a
guide.
2)
to an area ap-
proximately
g.
Place the window in
h.
Using
position
AN470AD4 rivets,
and cleco in
secure
place.
the window to the door.
NOTE
When
riveting the window in place, install the trim
d of the window removal procedure.
i.
Install the trim
j.
Clean and paint
k.
Install the center
i.
Install the inboard door handle, ash tray and
E18
strip clips
in the
same
locations
as
marked in step
strip.
as
necessary.
upholstery
pane.
arm
rest.
3-55
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
CENTER WINDOW REMOVAL AND INSTALLATION
a.
Remove the emergency release
b.
Removethe
c.
Installation is
pin.
hingepin.
accomplished by reversing
the above
procedure.
NOTE
Some hand
forming
may be
to obtain
required
a
proper fit.
AFT WINDOW REMOVAL
a.
Remove the
upholstery panel along
b.
Remove the
royalite molding around
c.
Remove the top, bottom and forward
d.
Remove the window.
bottom of the window.
the window.
retaining angles by removing
the
attaching
screws.
AFT WINDOW INSTALLA TION
a.
Clean the sealer from the canopy section where the old window
Materials Chart, Section
b.
Apply
sealer
the old sealer
(4, Sealing Chart,
was
Position the window and
d.
Install the
Section
2)
to an area
secure
royalite molding
in
and the
place
approximately
with the retainer
1/2 inch wide
on
the canopy section where
Remove the
b.
Remove the trim
c.
To facilitate installation, mark the location of the trim
d.
Remove the rivets from around the window.
e.
Removethe window.
strip
as
required
to
gain
access to
attaching
screws.
7H-I AND
AFTER)
the window frame.
from around the inside of the window.
strip clips.
THIRD OR FOURTH WINDOW INSTALLATION
(TE-768 AND AFTER;
Clean the sealer from the cabin section where the old window
terials Chart, Section
and retainer
(TE-766 AND AFTER;
a.
upholstery panels
angles
upholstery panel.
7HIRD OR FOURTH WINDOW REMOVAL
was
removed
using
7H-I AND
toluol
AFTER)
(20, Consumable
Ma-
2).
b.
Place the window in
c.
Remove the window and trim off the
d.
Place the window in
3-56
using toluol (20, Consumable
removed
removed.
c.
a.
was
2).
position
position
and mark the
areas
excess
and cleco in
where material must be removed to obtain
material
place using
as
a
proper fit.
determined in step b.
the
pilot
holes
provided.
818
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
e.
Back drill the window frame
using
the
existing
holes in the back section
f.
Remove the window, clean and deburr all holes and apply sealer
proximately 1/2 inch wide on the canopy section where the old sealer
g.
Using
AN470AD4 rivets,
secure
as a
guide.
(4, Sealing Chart,
was
Section
2)
to
an area
ap-
removed.
the window to the cabin section.
NOTE
When
step
riveting the window in place, install the trim
of the window removal procedure.
c
h.
Installthetrim
i.
Clean and paint
j.
Install the
strip clips
in the
same
location
as
described in
strips.
as
necessary.
upholstery panels.
FIBERGLASS
REPAIR OF FIBERGLASS COMPONENTS
a.
Large
holes and cracks
If the parts
cutout.
b.
are
Prepare
3
painted,
require
remove
the
that the
paint
damaged
area
and sand that
be cut out and trimmed
portion of
the
just beyond the area of damage.
part extending at least 2 inches beyond the
patches of laminated glass cloth, such as Trevano, Uniglass, or their equivalent. Cut the first patch
patch 1/2-inch smaller than the first, and the third patch 1/2-inch
to the dimensions of the sanded area, the second
smaller than the second.
c.
Prepare
the resin
(Laminac 4116, Glidpol 1001,
facturer’s instructions. Make
sure
that your hands
d.
or
are
their
equivalent)
for the
free of oil, grease,
or
patch in
dirt when
accordance with the
handling
manu-
the resin.
Apply an even coat of resin to the sanded area. Impregnate all three laminated glass cloth patches by laying
patches on clean waxed paper and working the resin through the fabric with a 2-inch brush.
Place the
the
large patch
over the cutout area, working out all air bubbles and wrinkles. If the patch starts to
sag,
behind
the
place support
repair area. Coat the support with automobile wax or waxed paper to prevent the resin
from adhering to the support. Work out all air bubbles and wrinkles, while installing the second
patch over the first.
Install the third patch over the second in the same manner.
e.
a
f.
Brush the
between 23"C
repair to
E18
repaired area with an even coat of resin. After the patches have cured for 24 hours at temperatures
(75"F) and 66"C (150"F), blend the patch into the contour of the part with fine sandpaper. Paint the
match the rest of the
part.
3-57
SECTION
FLIGHT CONTRO LS
AN D S U R FAC ES
BEECH BARON 55 AND 58 SHOP MANUAL
FLI G HT CON TRO LS A N D S U R FACES
CONTROL SURFA CES
WARNING
IW~RNING)
On
airplane
serials
TH-1389, TH-1396
ment pa rts, observe the color
and after and earlier
coding.
On these
airplanes
a i rp la n es
th e
with
new
cc ntro I ca b I es
spare replacebel I c ra n k a n d
other components are color coded. Do not connect coded parts of one color to coded parts
of a different color. Ensure that the primary and secondary controls are operating in the
proper direction.
NOTE
On at I contro I col umn systems and co nt ro I s u rf ace systems, the inside su rf ace of al I tu m buc kl es
must be coated with g rease (1 1 Consu mable Materials Chart, Section 2).
All
primary flight controls are cc nve nti o n a I c ab I e-ope rated su rf aces a nd are manually controlled through cablebellcrank systems. Each system includes surface travel stops and linkage adjustments. The optional electric elevator trim and wing flaps are driven by electric motors.
The
ailerons, elevators and rudder
can
be secured with control locks
(gust locks)
in the p i lot’s
com
to the GROUND HANDLING AND SERVICING section of this manual for control lock installation
partme nt. Ref er
procedures.
Ai rp lane serials TC-1 a nd afte r, TE-1 and after, TH-l through TH-1388 and TH-1 390 through TH-1 395 are equipped
with either a standard single throw-over control arm, or a dual control T column. On TH-1389 and TH-1396 and after,
dual controls are installed as standard equipment.
The
ru d de r
ped al s a re i nte rco n n ected by I i n kag e below the floor. The pedals are adj ustable to two positions by
pressing spring-loaded lever on the side of the pedal. If brakes are not installed on the copilot’s pedals, the same
leve r can be used to place the copi lot’s pedals agai nst the floo r.
a
The
wing flaps are operated by an electric motor-driven gearbox on the forward side of the rear spar at the centerline
airplane. The gearbox drives two flexible drive sh afts, each connected to an acme-th read-type jackscrew at
the flap. The flaps a re co nt ro I I ed by a lever (switch) on the instrument subpanel. The lever must be pulled out of a
detent to change positions.
of the
The
flap position transmitter, if installed, is located near the left flap actuator. On airplanes with the sing le th row-over
or the T control, the flap position is indicated by an instrument to the left of the flap control lever. On TH-1389
and TH-1 396 and after, the flap position is ind icated by three lights to the left of the flap control I eve r. Th e lights
indicate down, approach and in-transit positions. All lights are out when the flaps are up.
control
Trim tabs
are
installed
cable-drum systems,
The
optional
crossing
each elevator, the rudder and the left aileron. The tabs
using jackscrew
actuators. Tab
electric elevator trim tab is controlled
Positive stops
limit trim tab
on
on
the
primary flight
move me nt.
the cables and
Th e
by
position
a
indicators
are
are man
provided
ually
on or near
switch in the outboard handle of the
control led
through
the tab controls.
pi lot’s
co ntro I
whee I.
control surfaces limit their travel. Travel stops secured to the tab control cables
of cables as shown in the applicable ri g g i n g i I I u st rati on s will prevent
co rrect ro u ti n g
causing
incorrect movement after the cables have been removed
an d re i nstalled.
Control
movement and direction should be checked after maintenance.
Refer to the
and force,
E16
applicable rigging procedures for details regarding chain
downspring
and cable tension, control wheel movement
force and syste m frictio n.
4-1
BEECH BARON 55 AND 58 SHOP MAN UAL
EFFEC T OF TEMPERA TURE UPON CABLE TENSION
Graphs specifying the correct maximum
syste m rigg i ng i I I ustratio ns.
and minimum cable tension for the various controls appear
on
the individual
co ntrol
The
graphs provide tension limits at temperatures from 30"
designate the temperature at which the c o nt ro I cab les ca n
tension in pou nds for each temperature reading.
to 1 1 O" Fah renheit. The horizontal scales
be
rigged,
and the vertical scales
on
designate
the g raphs
the correct
CAUTION I
I cAuTlon
A control cable must be
any three foot segment.
replaced if it
is determined to have
more
than three broken strands
along
NOTE
When
I
inspecting
the cables
move
control cables, it is important to operate the controls through their full range so that
away from the pulleys and all portions of the cables are exposed for inspection.
TA PER PINS
When
installing taper pins,
shank must be flush with,
use a
or
lightwe ig ht
extend
no more
rawh ide
or
nylon mallet
to set the
pin.
The small end of the
tapered
than 0.06 inch above the surface.
cnvnow 1
I CAUTION
The
taperpin
can
crack the torque tube if it is driven too far.
SI N G LE TH R OW-OVE R CO NTRO L CO LU M N (O PTI O N A L O N TC-1 A N D AFTER; TE-1 A N D
AFTER; TH-1 THRU TH-1 388, TH-1 390 THRU TH-1 395)
FIGURE 4-1
CONTROL COL UMN ARM REMO VAL
I
a.
Remove the four
b.
Disconnect any electrical
wiring.
c.
Pull the T handle located
on
d.
Rotate the control column
screws
that
the retainer collar
secure
assembly
the forward side of the control
arm
to the
nearly
vertical
to the control column
housing.
arm.
position
and slide the control column
arm
off the
housing.
CONTROL COL UMN ARM INS TALLA TION
a.
Position the control
approximately parallel
each other
I
near
the
arm
in
a
vertical
to the sides of the
access
arm
to
Figure
4-1. Ensure that the slot in the lower
and the turnbuckles between the
long
and short chains
sprocket is
opposite
are
opening.
b.
The ailerons MUST be in the neutral
c.
Pull the T handle located
4-2
position. Refer
on
position.
the forward side of the control
arm.
E16
BEECH BARON 55 AND 58 SHOP MANUAL
d.
Slide the control column
e.
Connect all electrical
f.
Install the retainer collar and attach it with the four
g.
Check for full control column movement and for proper direction of movement.
arm on
the control column
housing.
wiring.
screws.
RIGGING THE CONTROL A Rhll CHAIN
Position the control arm, control wheel, and sprockets as shown in Figure 4-1.The long and short chains must
on the sprockets within one link. The turnbuckles must be near the access opening. The slot in the lower
a.
be centered
sprocket
b.
should be
Remove the
approximately parallel
to the sides of the arm.
wire from the turnbuckles and loosen
safety
or
tighten
the chain
as
necessary.
NOTE
Tighten
enough
the chain until friction
to
remove
the
binding
or
or
binding
is felt
on
c.
Check the control wheel and control surfaces for proper
d.
After the adjustments
to
Figure
e.
are
complete,
the control wheel, then loosen the oh ain
just
friction from the control wheel.
operation
and freedom of movement.
check the location of the control wheel,
sprockets,
and turnbuckles. Refer
4-1.
Safety
wire the turnbuckles.
NOTE
serials TC-1 482 t h rou g h TC-2456, TE-881 throug h TE-1 201 TH-265 th roug h TH-1388
and TH-1 390 throu gh TH-1395 have roller-type chain and sprockets installed in the control col umn
Airplane
arm.
Modification of earlier models from the silent
type chain and sprocket
pe rfo rm ed i n accordance with Beech Se rvi ce I n st ru cti ons No. 0523 -1 55
instructions
are
or
type
s u bs eq u e nt.
can
be
Rigging
I
identical for both types of wheel.
DUAL CO NTRO L ARM
TH-1 388, TH-1 390
to the roller
(O PTI O N A L
THRU TH-1 395)
ON TO-1 A N D AFTER; TE-1 AND AFTER; TH-1 TH R U
FIGURE 4-2
DUAL CONTROL ARM REMO VAL
a.
Remove the four
b.
Disconnect the electrical
c.
Remove the
screws
screw
that
secure
the retainer collar
assembly
to the control column
housing.
wiring.
and washer
retaining
the
pin assembly
on
the
right
forward side of the control
arm.
NOTE
So me i nsta I lati o n s have
a
T handle
on
the
installations, pull the T handle and omit step
d.
E16
Slide the control
arm
off the
rig ht
fo rwa rd side of the dual control
arm.
On these
c.
housing.
4-3
BEECH BARON 55 AND 58 SHOP MAN UAL
i
c~L:
u
__
LONG
CHAIN
OPENING
ACCESS
TURNBUCI~LE
SHORT
SLOT
IN
CHAIN
SPROCKET
C9201738
Single
(TC-1
4-4
Throw-Over Control Column
and After; TH-1 thru TH-1388, TH-1390 thru
Figure 4.1
TH-1395)
E16
BE EC H BARON 55 AND 58 SHOP MAN UA L
DUAL CONTROL A RM INS TA LLA TION
a.
Position the control
b.
Ensure that the slot in the center
and the short chains
c.
The
a i le ro n s
arm as
shown in
opposite
are
Figure
sprocket
each other
is
4-2.
approximately vertical and
the access openings.
the tu mbuckles between the
long chains
near
M U ST be i n neutral.
NOTE
So me i n stal I at io ns have
T handle
a
on
the ri g ht fo rwa rd side of the d u al control
installations, pull the T handle and omit step
d.
Slide the control column
e.
In stall the
f.
Install the retainer collar and attach it with the four
g.
Check for full control movement and for proper direction of movement.
pin assembly
arm
on
onto the control column
the
right
arm.
On these
I
e.
housing.
side of the center control
arm
hub.
screws.
RIGGING THE DUAL CONTROL ARM CHA IN
a.
Position the control arm, control
b.
Center the
c.
The slot in the center
d.
Remove the
e.
Adjustthe
long
wheel, and sprocket
and short chains
safety
chains
sprocket
on
their
must be
sprockets
as
shown in
within
approximately
one
Figure
4-2.
link.
vertical. Refer to
Figure
4-2.
wire from the turnbuckles.
as
necessary.
NOTE
The chains
are
properly adjusted by tighten the chains until binding is noticed on the control wheel,
just enough to remove the binding or friction from the control wheel.
then loosen the chains
f.
After the
turnbuckles
g.
Safety
adjustments
are as
complete,
Figure 4-2.
are
shown in
check that the location of the control arm, control wheels,
sprockets
and
wire the turnbuckles.
Check the controls for freedom of movement and the control
D UA L CO NTR O L CO LU M N S
Fi G U R E 4-3
r~H-l 339,
su rfaces
for proper direction of
move ment.
TH-1 396 AN D A FTE R)
CONTROL COL UMN CHAIN REMOVAL
NG URE 4-4
a.
Paint
one
tooth
on
each control column
sprocket
and its
corresponding
chain link to
ensure
correct
alignment
of the control wheel at installation.
E16
4-5
BE ECH BARON 55 AND 58 SHOP MA N UAL
MUST
TURNBUCKLES
BE OPPOSITE
SLOT
LONG
CHAIN
II
IN
SPROCKET
I
IONG
CHAIN
g~a:
SHORT
TURNBUCKLES
OPPOSITE
CHAIN
MUST
LEE
RIGHT
LEFT
VIEW
LOOKING
AFT
RIGHT
LEFT
DETA IL
A
FWD
C9201739 C
Dual Control Column Chains
(TC-1
and
After;
TE-1 and
After;
TH-1 thru
Figure
4-6
TH-1388, TH-1390
thru
TH-1395)
4-2
E16
BEECH BARON 55 AND 58 SHOP MAN UAL
the control column chain.
b.
Loosen the tumbuckles
c.
Remove the saf ety wi re from the fou r bolts
on
(two on each end)
and
the six bolts from the chan nel between
remove
the control colu mns.
d.
Remove the channel from the
e.
Disconnect the tu mbuckles from the control colu mn chain.
f.
Remove the four connector links from the link
airplane.
assembly, and
remove
the link
assembly.
NOTE
It may be necessary to
g.
Slide the
sprocket support assemblies
remove
the stop before
aft
the
over
U-joints
removing
and
remove
the link
assembly.
the chains from the control columns.
CONTROL COL UMN CHA IN INSTA LLA TION
FIGURE 4-4
a.
Install the chains
sponding
marks
on
over
the
the control column
sprockets.
The
painted
marks
on
the chain must
align
with the
corre-
sprockets.
Install the control column chain in the outboard holes of the link
b.
Install the link
c.
Install the aileron cable chains in the inboard holes of the link
assembly.
assembly.
assembly.
NOTE
Make certain the connector links
installed
correctly.
removed.
d.
Install the stop if it
e.
Connect the tu mbuckles, but do not
f.
Slide the
was
are
tig hte n
sprocket support assemblies
them.
forward and install the channel between the control columns.
Safety wire
the bolts.
g.
Tighten
the control colu mn chains
as
described in CONTROL CO LU M N CHAIN RIGGING.
WARNING
IWARNING)
Check the ailerons for correct direction of movement. When the control wheel is moved to
move up and the right aileron must move down. When the
the left, the left aileron must
control wheel is moved to the
move
E16
right,
the
right aileron
must
move
up and the left aileron must
down.
4-7
BE ECH BARON 55 AND 58 SWOP MANUAL
1. WHEEL
2. COLLAR ASSEMBLY
3.
4.
5.
6.
7.
8.
9.
10.
11.
1 2.
13.
1 4.
15.
16.
17.
18.
19.
20.
COLUMN TORQUE TUBE
ELEVATOR TORQUE ARM
ELEVATOR TORQUE TUBE
ELEVATO R BELLCRANK
ELEVATOR TORQUE TUBE SUPPORT
BOB WEIGHT ASSEMBLY
COLLAR
COLLAR ASSEMBLY
ELEVATOR PUSHROD
CON NECTOR
INNER COLUMN GUIDE
INNER COLUMN TO ROUE TUBE
20 21
UJOINT
SPROCKET SUPPORT
19
TAPER PIN
18
SPROCKET
FORWARD SUPPORT
NUT
21. COTTER P1N
22. SUPPORT ROLLERS
I
1
16
14
1j
4
12
15
j
1
17
Q~D
ii
17
1
3
1
22
>s~l
8I
17
j
17
1
c
36-~5C14
Dual Control Columns
(TH-1389
and TH-1396 and
Figure
4-8
After)
4-3
El 6
BE ECH BARON 55 AND 58 SHOP MAN UAL
CONTROL COL UI~IN CHA 1N RIG GING
FIG URE 4 -4
Rig
a.
neutral
on
must be
aligned
b.
e nds
The
ce nte rl i ne
d.
on
Adjust
Rig
straightedge
a
across
the tops of both cent ro I wheels. The
grips
right sprocket
must be eq u id i stant, with i n
one
ii n k, f ro m the
sprocket.
assembly
must be centered within 0.20 inch with
respect
to the
the turnbuckles to obtain 0.1 9 to 0.31 inch of deflection with
the upper control column chain
e.
by securing
of the control column chain around the
of the
The link
c.
the control wheels
within 0.06 inch.
the aileron control system
the
near
as
airplane
stop.
p ress u re of 1 .50 to 2.50 pou nds
a ve rtical
centerline.
described in R IGG ING TH E Al LE RON CONTROL SYSTEM.
CONTROL COL UMN ROLLER ADJUSTMENT
FO RWAR D O UTER-TU B E ROLLERS
(ROLL
ON THE SQUARE IN NER
SHAFT)
FIGU RE 4-5
There
are
four rollers
on
the fon~vard end of each control column which transmit torque to the square inner shaft.
are installed with eccentric bolts which allow for adjustment of roller clear-
Two of the rollers for each control column
ance.
These two bolts may be identified
by their
10-32 threads.
Adj ust the
rollers
as
fol lows:
TURNBUCKLE
STOP
TORQUE
SHAFT
GUARD PIN
LINK
ASSEMBLY
CHAIN
ASSEMBLY
I
CONNE CTOR
SPROCKET
LINK
ASSEMBLY
AILERON CABLE
ASSEMBLY
AIRCRAFT
36-155-6
Dual Contro I Column Chain
(TH-1389,
TH-1396 and
Figure
El 6
Rigging
After)
4-4
4-9
BEECH BARON 55 AND 58 SHOP MAN UAL
a.
Wipe
b.
Hold
c.
The roller
d.
If the conditions of
the shafts clean and
one
of the
on
the bolt until in
the
nonadjustable
opposite
step
compliance
Tighten
f.
Check the other
g.
If the
procedure
the shaft.
firmly against
side of the shaft should turn
c are
freely while having
as
aftertightening (steps
indicated in steps b and
b and
c).
c.
needed for the second set of rollers, follow steps d, e, and f.
for the other control column.
The top two rollers of each cent rol colu m n s u pport
ment. Check the roller adjustment as follows:
a re
(ATTACHED TO
i nstalled with
Pull the control column fore and aft until the
THE INSTRUMENT
ecce ntric
position of least clearance
Keep the control column in this position while checking
probably have its own position of least clearance.
is located.
column will
than 0.002 inch of clearance.
c.
CONTROL COLUMN SUPPORT ROLLER ADJUSTMENT
ers
no more
not met, loosen the nut on the roller which has the bolt with 10-32 threads. Turn
with the conditions of step
pair of rollers
adjustment is
this
rollers
the nut. Recheck the roller clearance
e.
Repeat
dry.
bo its which
Hold the control column
b.
The clearance between the control column tube and the lower roller should be 0.005
c.
If the correct clearance is not indicated loosen the nuts
d.
Rotate the bolts to obtain the proper clearance.
two
b e used fo r
adju st-
between the control colu mn and support rolland/or adjusting the clearance. Each control
a.
firmly against the
m ay
SUBPANEL)
top rollers.
on
0.002 inch.
the two top rollers.
FORCE
THIS ROLLER
SHOULD ROLL
FREE
.002 OR LESS
36-150-4
Forward Control Column Rollers
Figure
4-10
4-5
El 6
B E EC H BARON 55 AND 58 SHOP MAN UAL
the nuts.
e.
Tigh ten
f.
Recheck for proper clearance
g.
Repeat fo r the
other
(step b).
co ntro I co I u m n.
AILERON SYSTEM
A ILERON REMO VA L
Disconnect the lower aileron tab
a.
push-pull
rod
(left
aileron
only).
NOTE
Lowering
b.
Support
c.
Pull the aileron
i ng cable
d.
the aileron and
the
flaps
remove
will aid in
the two
disconnecting
attaching
screws
the aileron tab
push-pull
rod.
from the top and bottom of each
straight away from the wing to avoid damage to the attaching
areas
and
hinge
gain
bracket.
access
to the bond-
sc rews.
Remove the
screws
attaching
the
bonding
cable to the aileron.
AILERON INS TA LLA TION
NOTE
If the ai le ron tab has bee n removed and reinstalled, or a new tab installed, lubricate the tab hinge
(preferred) or CRC 3-36, LPS-1 or WD-40 (50, Consu mab le Materials Chart,
with VV-L-800A
Section
2).
a.
Attach the
b.
Place the aileron in
bonding
aileron skin and the
cable to the aileron.
position on the hinge
reinforcing structure.
Install the upper and lower
c.
d.
Pull
cc
rrectly.
e.
hinge
brackets. The
bracket
hinge
brackets must be in the correct
place
screws.
the aileron in a direction straight away from the wing to make sure that the hinge brackets
If there is any movement of the aileron, recheck the position of all hinge brackets.
on
Connect the aileron tab
push-pull
between the
rod and install the cotter
pin (left
aileron
are
positioned
only).
NOTE
Lowering
the
flaps
will aid in
connecting
the aileron tab
push-pull
rod.
RIGGING THE A IL ERON CONTROL S YS TEM
A ND A FTER; TE- I AND AFTER; TH- I THRU TH- 1 386, TH- 1 390 THRU TH- 1 395)
FI GURE 4-6
(TC- I
NOTE
Beech recommends the
use
of the aileron travel gage shown in the GEN ERAL IN FOR MATION
wing station 122.75.
section of this manual. Locate the travel gage at
616
4-11
BEECH BARON 55 AND 58 SHOP MAN UAL
a.
Aileron and
b.
Check the aileron for lost motion at the
flap surfaces
must
align
with the up per and lower surfaces of the
midpoint
of the
trailing edge
wing
within 1/1 6 inch.
with the bellcrank
stationary.
The maximum
allowable lost motion is 1/16 inch.
point hole for the cable is 1.9 to 2.0 inches from
trailing edge aligns with the trailing edge of the wing, and
its in boa rd end is parallel with the outboard end of the flap. A horizontal misalignment of
3/16 inch is allowed between the trailing edges of the aileron and wing. If the aileron is not in neutral, adjust the length of the ai le ron pus hpull tube. Loosen the locknuts of both ends and turn the tube to shorten or lengthen. Tighten the locknuts. Repeat
the procedure for the right aileron.
Position the left aileron bellcrank
c.
so
the
adjacent rib.
d.
Place th e cent ro I wheel i n neutral
that the center of the attach
The aileron is in neutral when the aileron
the top of the control wheel with
by leveling
a s
pi rit
level.
NOTE
co ntro I w h ee I m u st
The
corresponding change
be leve I i n relation to the ai rplane. If the
to the
position
of the control wheel
e.
Adjust the
tu mbuckles in the wheel wells to
f.
Adjust the
travel
stops (primaly stops)
on
bring
the
right
using
a
a i rp I ane
spirit
is not level, make
a
level protractor.
and left ailerons to neutral.
both aileron bellcranks to obtain 19" to 21" of deflection in each direc-
tion.
g.
Tighten
h.
Rig
i.
Be
its
the locknuts
on
both stop bolts for the bellcrank.
the aileron cables to the tension shown in
sure
Figure
4-6. Use the turnbuckles in the wheel wells.
each aileron bellcrank contacts its upstep at the
same
time the bellcrank in the
opposite wing
contacts
downstop.
Check the control stop (secondary stop) in the control column for 0.12 to 0.18 inch clearance in each direction.
If the clearance is not correct, recheck the entire aileron control system for correct chain and cable rigging.
j.
NOTE
The control stop clearance provides a slight movement of the control wheel
on the aileron bellcranks make contact.
(a "cushion")
after the
travel stops
k.
Recheck cable tension and
safety
wire the turnbuckles. Be
sure
that all locknuts
are
tight.
WARNING
IWI~RNING)
Check the ailerons for correct direction of movement. When the control wheel is moved to
the left, the left aileron must move up and the right aileron must move down. When the
co ntro I whee I is moved to the right, the right aileron must move up and left aileron must
move
4-12
down.
E16
ERMYRRROGW Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
..A-
RIGHT AILERON UP
i.~I
DETAIL
RIGHT AILERON UP
F.S. 96.80
C
i:
84.358
s
J
DETAIL
F.S.
FUSBAGE STAflON
CABLE
DETAIL
D
LEFT AILERON UP
B
BALANCE CABLE
F3. 117.187
f.\
D
~b
F--
LEFT AILERON
112.000
tC~C
UP7
AILERON TAB
ACTUATOR
~4
TEMPERATURE CABLE TENSION GRAPH
AILWON AND AILWON TAB CABLES
LEFT WING DOWN
B
A
40
CABLE TENSIONS BASED ON 5B"F AMBIENT
fRAVEt STOPt
BALANCE CABLE
WING; DOWN
~t
E
F.S. 68.00
~LER
F
A
L~U
Z
WING DOWN
~tl
FWDI
DETAIL
I
--I
AILERO N
BELLCRANK
RIGHT WING DOWN
DETAIL
10
F
30
W.S. 23.881
40
50
1-
TEMPERATURE CABLE fENSION GRAPH
H-14 AND SP:3 AUTOPILOT AILDION CABLES
,-r
W.S. 34.375
CABI FTENSIONS BASED ON gg’F AMBIENT AIR TEMPERATURE
60
70
BO
90
100
110
TEMPERATURE SE
TEMPERATURE CABLE TENSION GRAPH
KFC 200 AUTOPILOT AILERON CABLES
CABLE TENSIONS BASED ON 59"6 AMBIENT AIR TEMPERATURE
w. S. 45.oOo
z
B
(i´•
W.S. 66.000
z
o
o
DETAIL
to
E
Y
w.s. W.094
30
40
50
70
06F’
80
90
100
;MINIMU~
llD
TEMPERATURE
NOTE. RIG AUT~RILOT CABLES AFTER CONTROL SYSTEM CABLES
ARE RIGGED
W.S. 108.281
AILERON TAB
ACTUATOR
30
40
50
60
70
8)
90
100
110
TEMF~ATURE "F
NOTE: RK; AUTOPILOT CABLES AFIER CONTROL SYSTEM CABLES ARE RIGGED
66-161-71\
Rigging the Aileron Control System
CTC-I and After; TE-1 and After; TH-1 thru
TH-1388, TH-1390 thru TH-1395)
Figure 4-6
E16
4-13
BE ECH BARON 55 AN D 58 SHO P MAN UAL
THIS FAG E I NTE NTI O NA LLY LEFT B LAN K
4-14
E16
BE ECH BARON 55 AND 58 SHOP MAN UAL
RIGGING THE A ILERON CONTROL SYSTEM
(TH-1 389,
TH- 1 396 AND
AFTER)
FIG URE 4- 7
WARNING
/W~RNINGI
When
replacing
installing
or
control
components, observe the color coding
to coded parts of a different color.
on
cables, bellcranks and other control system
all parts. Do not connect coded parts of one color
NOTE
Beech recommends the
use
of the aile ro n
travelgage shown in the
wing station 122.75.
GENE RAL IN FOR MATION
section of this manual. Locate the travel gage at
with the upper and lower surfaces of the
Aileron and
b.
Check the aileron for lost motion at the
flap
surfaces must
align
a.
midpoint of the trailing edge
wing
within 1/16 inch.
with the bellcrank
stationary.
The maximum
allowable lost motion is 1/16 inch.
point hole for the cable is 1.9 to 2.0 inches from
trailing edge aligns with the trailing edge of the wing, and
its inboard end is parallel with the outboard end of the flap. A horizontal misalignment of rt 3/16 inch is allowed between the trailing edges of the aileron and wing. If the aileron is not in neutral, adjust the length of the aileron pushpull tube. Loosen the locknuts on both ends and turn the tube to shorten or lengthen. Tighten the locknuts. Repeat
Position the left aileron bellcrank
c.
the
adjacent
the
proced u re
d.
Secure
ging.
so
that the center of the attach
rib. The aileron is in neutral when the aileron
a
fo r the
rig ht
straightedge
ai le ron.
across
the tops of both control wheels. Check the control columns for correct chain
the turnbuckles in the wheel wells to
e.
Adjust
f.
Remove the
straightedge
g. Adjust the travel stops
tion.
bring
(primary stops)
on
R ig the ai I e ro n cables to the tension shown in
its
Be
sure
and left ailerons to neutral.
both of the stop bolts for the aileron bellcrank.
i.
on
right
both aileron bellcranks to obtain 19" to 21" of deflection in each direc-
Tighten
the locknuts
the
from the control wheels.
h.
j.
rig-
Referto CONTROL COLUMN CHAIN RIGGING.
Figure
4-7. Use the turnbuckles in the wheel wells.
each aileron bellcrank contacts its upstep at the
same
time the bellcrank in the
opposite wing
contacts
downstop.
k.
Adjust
tween the
I.
E16
the
secondary stop
bolts
on
the link
assembly
at the forward end of the control column. Clearance be-
stop and each stop bolt must be 0.19 to 0.31 inch with the ailerons at full travel in either direction.
Rec heck cable te ns io n and
safety
wire the turnbuckles. Be
sure
that all locknuts
are
tight.
4-15
BEECH BARON 55 AND 58 SHOP MANUAL
With the aileron control system fully rigged, the torque
neutral must not be over 15 inch-pounds.
m.
required
to move the control wheel 10"
right
and left of
WARNING
/WARNING(
Check the ailerons for correct direction of m ovem ent. When the control wheel is m oved to
the left, the left aileron must move up and the right aileron must move down. When the
control wheel is moved to the right, the right aileron must move up and the left aileron must
down.
move
AILERON TRIM TAB RIGGING
NOTE
of the aileron trim tab travel gage shown in the G EN ERAL
IN FOR MATION section of this manual.
Beech
recommends the
use
a.
Place the aileron trim tab control in neutral.
b.
R e move th e
c.
Place the aileron in neutral.
ace ess
plate
to the trim tab actuator.
the chain from the trim tab actuator sprocket. By turning the sprocket, move the
trim tab actuator to both extremes of travel. Measure both settings and return the trim tab actuator to the midpoint
of the two extremes of travel. This places the trim tab actuator in neutral.
d.
Loosen the cable and
e.
If the trim tab is not in neutral,
f.
Center the chain
g.
Rig
h.
Adjust
i.
Check trim tab travel.
on
remove
the
the cable tension
as
adjust
sprocket
and
shown in
the
length
tighten
Figures
of the tab
push-pull
place
the trim tab in neutral.
the cable.
4-6 and 4-7.
the cable stops for the aileron trim tab to obtain 9" to 1 1" of
Safety
rod to
su rface
deflection in
eac h
d i rectio n.
wire all turnbuckles and cable stops.
NOTE
the aileron and ai le re n tri m tab control systems, check for correct move m e nt of the
control surfaces with respect to the controls. Since the aileron trim tab is a servo tab, the tab moves
is moved to RIG HT WING UP, the tab
up when the aileron moves down. When the trim tab control
moves down.
Afte r
riggi ng
A ILERON TRIM TA B A CTUA TOR REMO VA L
plates
at the actuator.
a.
Remove the
b.
Loosen the cable and
c.
D isconnect the actuate r from the tri m tab I in kage.
d.
Rem ove the bolts
4-16
access
remove
attaching
the chain from the actuator
the actuator to the
wing
sprocket.
structure. Remove the actuator.
E16
RalBheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
WING STATION
FUSELAGE STATION
W. S.
FS.
F.S. W).M)
RUDDER TAB CABLES
RIGHT AILERON UP
AILERON TAB CABLE
ELEVATOR CABLES
DETAIL
AILERON TAB CABLE
B
RIGHT AILERON UP
ELEVATOR TAB CABLES
F.S. 115.00
DETAIL
i:
BALANCE CABLE
LEFT AILERON UP
G
BALANCE CABLE
i)
--i~
DETAIL
A31E~
F.S. 117.187
C
D;TAIL D
-D
F.S. 112.000
LEFT AILERON UP
AILERON TAB
ACTUATOR
TEMPERATURE CABLE TENSION GRAPH
ALWON AND A~BON TAB CABLES
~Ct
bl~
~J
CABLE
TE~ONS
BASED
ON_58’F
AMBENT AR TEAAPERATL~9
B
BALANCE CABLE J
F
TRAVEL STOPS
i’l
to
MTAILA
3)
G
W.S ZjSS1
DETIILF
1~
W.S. 66.000
q
z
w.S. 94.094
80
70
g]
00
100
110
70
80
90
TEMP~ATCAE "F
NOTE: RIG AUTBILOT CABLES AF~ER CONTROC
SYSTEM CABLES ARE RC(YD
100
110
TEYPERATURE CABLE TENSION GRAPH
IQC 200 AUMPILO’T AILERON CABLES
AILERON
BELLCRANK
W.S. 45.000
z
50
60
i-
W.S. 34.375
CABLE KNSIONS BASU) ON 50"5 AMBEKT AW
40
50
rrhWUTUR F
TEMPERATURE CABLE TENSION GRAPn
H-14 AND SP-3 AUTOPhOT ALWON CABLES
30
40
DETAIL
CABLE TENSIONS BASED_ON 99"5 AMBEM AR rr~WAfUC(E
B~
x
w
t
30
E
w.s. ios.281
AILERON TAB
ACTUATOR
40
50
60
70
90
loo
l~o
TEMARATURE’F
NOTE: RIG AUTOPILOT CABLES AFTER CONTROL
SYSTEM CABLES ARE RIGGED.
58-151-36
Rigging the Aileron Control System
CTH-1389, TH-1396 and After)
Figure 4-7
E16
4-17
BEECH BARON 55 AN D 58 SHOP MAN UAL
THIS PAGE INTENTIONALLY LEFT BLANK
4-18
El 6
BE ECH BARON 55 AND 58 SHOP MAN UAL
AILERON TRIM TAB A CTUA TOR INS TALLA TION
a.
Position the actuator against the
b.
Follow the
wing
structure and install the
attaching
bolts and reconnect the tab
linkage.
procedure described in AILERON TRIM TAB RIGGING.
AILERON TRIM TAB A CTUA TOR DISA SSEMBL Y
a.
Remove the
sembly.
Refer to
pins from the
Figure 4-8.
b.
Remove the snap
c.
Remove the actuator
d.
Remove the
(11) from
the
ring (10)
(8).
(8)
from the nut
the actuator
The
e.
Remove the check nut
f.
Remove the
bearing (4)
(2),
bearing (4)
and
from the actuator
screw
pins from
screw
assembly (5)
nut
and
screw
sprocket (1)
housing (6),
and
and
the
remove
pull
the nut
sprocket (1) from the
assembly (5)
out of the
actuator
as-
housing.
assembly.
(8) and the actuator rod end (11) and remove the actuator
bushing (9) can now be removed from the screw.
rod end
and the
screw
from the nut
out the
adjusting bushing (3)
with
a
spanner wrench.
assembly.
AILERON TRIM TAB ACTUA TOR CLEANING AND INSPECTION
a.
Clean all parts with solvent
distortion.
b.
Replace the bushings
c.
Lubricate the actuator
Section
2)
before
(15, Consumable Materials Chart, Section 2),
and any
screw
parts showing evidence of
threads and the
and
inspect
for cracks, corrosion and
wear.
bearings with lubricating
grease
(1 1 Consumable
Materials Chart,
assembly.
AILERON TRIM TAB A CTUA TOR A SSEMBL Y
NOTE
During assembly lubricate
a.
Install the
b.
Install the other
c.
Install the actuator
d.
Push the nut
e.
Use
housing
actuator.
bearing (4)
on
the nut
bearing (4)
screw
assembly
and
moving parts with
assembly (5).
bushing (9)
in the nut
on
grease
Refer to
(11, Consumable
Figure
the actuator
Materials Chart, Section
2).
4-8.
screw
(8).
assembly.
into the actuator
housing (6),
and install the snap
ring (10)
in the
housing.
a spanner wrench to install the
adjusting bushing (3) into the housing until the end play between the screw
and nut assembly is less than 0.025 inch. If the end
play cannot be reduced to within limits, replace the
f.
Install the check nut
g.
Install the actuater rod end
h.
Align
E16
all
(2)
the holes in the
on
the
screw
adjusting bushing.
(Il)on
(8)
the
screw.
with those of the actuator rod end
(11)
and install the two
pins.
4-19
BEECH BARON 55 AND 58 SHOP MANUAL
Install the sprocket
j´•
Align
(1)
the holes in the
on
the actuator
assembly.
sprocket (1) with those in the
nut
assembly (5)
and install the two
pins.
CHECKING A lL ERON TRII1I1 TAB FREE PLA Y
FIG URE 4-9
Visually inspect
the aileron trim tab for
syste m. I nco n s iste nc ies
A ch eck fixtu re
loading
m ust
damage, security of hinge attach points, and
checking the free play of the tab.
for
tightness
of the actu ating
be corrected before
(P/N 45-135030-9/810) or equivalent a d ial ind icato r, and a push-pull scale for applying
are required for making the inspection for tab free
play. Refer to Figure 4-9.
accurate
to the tab
Securely
lock the control surfaces to prevent movement of the ailerons. Set the aileron trim tab in neutral.
b.
Use shot
bags
tab
hinge
a.
line and
to hold the dial indicator check fixture so that the
on
the outboard
edge
point
of the dial indicator is 2.0 inches aft of the
of the aileron tab.
c.
Apply a small piece of masking tape (for paint protection) 4.0 inches aft of the tab hinge line and
terline of the tab actuator. This is the point of
pressure against the tab by the push-pull scale.
i. Sprocket
8.
9.
10.
11.
1.2.
13.
’2. Check Nut
3. Adjusting Bushing
4. Bearing
5. Nut Assemb~y
6. Actuator Housing
7. B rac ke t
along
the
cen-
Actuater Sc rew
Bushing
Snap Ring
7
Actuator Rod End
8
Tube End
Actuator Tube
jCQ
3
4
5
13
10
9
4
12
11
rrn7e
984869AA
Aileron Trim Tab Actuator
Figure
4-20
4-8
51 6
BEECH BARON 55 AND 58 SHOP MANU AL
9
12
to
678
13
ii
5
j
.8 IN
j
P.Ii
.5 IN
iii
TAP
5/8-11
.25 IN
O
1.25
1
_TYP
_
_
___
a.9 iN
_
~A t t-L
4
TAB
14
/I‘lt15"
1.30 IN
ITEM
QUANT.
DESCRIPTION
rr
t
NO.
.68 IN
3/4
1
6 aluminum
equiv.
1
2
2
2
1
3
1
1/2
4
1
C81Q Indicator"
5
1
3/4
6
1
1/4 Dia. x 2 corrosion res. stl.
7
1
1/4 Die. xlcorrosion res. stl.
8
1
1/4-28 nut
x
x
x
1 3/8
x
x
2 112
x
x
10 aluminum
14 aluminum
1
3/8
x
5
x
1
3/8
x
2
x
10 rubber
11
1
1/4
x
2
x
10 corrosion
12
2
1/2
x
13
13
2
KN813 Keensert
14
2
1/8
"PM of Federal Products
equiv.
equiv.
or
equiv.
or
-t--H
c
1.6 IN
.31 IN
10 rubber
9
10
x
or
t 3/4 aluminum
x
7 1/2
or
x
3 VLIER
or
1 x 3/4 rubber
Corp., Providence.
R. I.
res.
Torque
tap 1/2
stl.
~ic
screw
sE CTION
13
I
I
A A
d THIS GROOVE TO BE A SNUG FIT
TO THE SCREW BRACK~T ON
THE DIAL INDICATOR
loo.lss-s
Fabricating Clamp for Tab Deflection
Figure 4-9
Fl 6
4-21
BEECH BARON 55 AND 58 SHOP MAN UAL
d.
Apply
e.
Set the dial indicator at
f.
With the
g.
Release half of the load to obtain
h.
On the
i.
Release half of the load to obtain
a
j.
E nte r t he
copy of Chart 4-1 and p roceed
another
of
piece
push-pull
masking tape
zero.
scale
masking tape
on
on
the
masking tape, apply
the bottom surface,
2 and record
2.
Subtract A from 28 and record
3.
Multiply
4.
Subtract C from 2D and record
by
2 and record
as
as
a
3.0
during
pound
on
the
the bottom surf ace of the tab.
checking procedure.
downward load. Record the dial
1.5
apply
a
3.0
pound upward
pound upward
load. Record the
as
reading
as
as
as
A.
B.
load. Record the dial
reading
reading
reading
as
C.
D.
fo I lows:
28.
Multiply
D
location
1.5 pou nd downward load. Record the dial
a
1.
by
corresponding
Do not reset the dial indicator
reco rded re ad i n g s o n a
B
in the
as
X.
2D.
as
Y.
NOTE
X and Y
Add X and Y and record
as
can
be
negative
numbers.
E.
C HA RT 4-1
Al LE RON TA B FREE PLAY LIM ITS
1.5-POUND
8-POUND
READING
READING
2B
-A
=X
2D
-C
=Y
X
+Y
=E
E
k.
If the free
play
is
over
the maximum
to determine the cause. All worn
parts
0.094 inch maximum
specified in Chart 4-1, inspect
replaced.
all components of the tab actuator
system
must be
E LEVATO R SYSTEM
ELEVA TOR REMO ~AL
NOTE
Refer to Beech Service Instructions No. 0636-133 for
fittings
4-22
on
airplane serials
inspection of the elevator hinges and torque
through TE-848 and TH-1 throug h TH-1 84.
TC-1 th rough TC-1 41 4, TE-1
El 6
BEECH BARON 55 AND 58 SHOP MAN UAL
navigation light
and
a.
Detach the tailcone. Disconnect the wire for the tail
b.
Remove the tail section
c.
Remove the
d.
Disconnect the elevator
e.
Disconnect the elevator trim tab actuator rods from the elevator trim tabs.
f.
Disconn ect the elevator
attaching
access
doors
on
the left side of the
nuts at the elevator
push-pull
bonding
remove
the tail
cone.
fuselage.
hinge points.
tubes from the elevator to rque
cable. Remove the
hinge
fittings.
bolts and
remove
the elevator.
ELEVA TOR INSTALLA TION
the stabilizer and install the elevator
a.
Position the elevator
b.
Connect the elevator trim tab actuator rod to the trim tab.
c.
Installthe
attaching
on
nuts at the elevator
hinge points. Torque
hinge
bolts. Connect the elevator
the center and outboard
bonding
hinge bolts
cable.
to 20 to 25
inch-pounds.
NOTE
If cotte r p i n holes
tighten beyond
d.
Torq ue
the in board
aligned
inch-pounds.
are
40
hinge
not
cc nti n u e
bolt to 30 to 40
ti g hte n i n g
u nti I
the cotte r p in may be i ns e rte d. Do not
inch-pounds.
NOTE
pin holes are not aligned
tighten beyond 70 inch-pounds.
If cotter
e.
Connect the elevator
f.
Install the tail
cone
push-pull
co nti n ue
tig hten in g
tube at the elevator torque
and connect the
navigation light
unti I t he cotter
pin
may be inserted. Do not
fitting.
wires. Install the
access
doors.
ELEVA TOR SKIN REPLACEMENT
(TC-54 7 A ND A FTER;
TE- I A ND A FTER; TH- I A ND A FTER)
1
FIGURE 4-10
NOTE
airplane serials TC-1 through TC-546 have skins that are riveted to the ribs. These
for bonded
can be replaced using best sheet metal practices. The following procedure
not apply.
The elevators
on
elevator skins
skins does
point where skin replacement is required, it is possible to replace
Replacement must be made only by an experienced sheet metal mechanic in a fully equipped
using the following procedure.
If
an
E16
elevator is
damaged
to the
one
orboth skins.
sheet metal
shop
4-23
BE ECH BARON 55 AND 58 SHOP MANUAL
NOTE
The
must be fabricated for
following special tools
holding fixture which attaches
skin removal and replacement.
A
clamping
A tool for
bucking
a.
Remove the
damaged
to each of the elevator
replacing
hinge points
one or
a
through
handle
long enough
to reach from the
both elevator skins:
and holds the spar
trailing edge of the elevator while the bonding material
also hold the trailing edge straight.
bar with
skins to the rivets
when
the
4-10. This tool must
A small
use
cures.
trailing edge
rigid during
Figure
Refer to
down between the
the spar.
elevator from the
airplane.
CAUTION I
I CAVTION
both skins from the elevator at the same time. If both skins are to be replaced, one
skin must be removed and the replacement skin installed on the eleva tor before the other skin is
Do not
remove
removed.
holding
fixture.
b.
Install the elevator in the
c.
Remove the forward outboard elevator
d.
Remove the elevater tab.
tip
cove r.
NOTE
Use the correct size drill bits when
removing
rivets to avoid oversize holes in the structure.
along the trailing edge of the elevator.
e.
Drill out all the rivets
f.
Drill out the rivets that attach the skin to the ribs and tab
g.
Use
a
thin
sharp putty knife
or
hinge bracket.
equivalent tool to cut through the
bonded
area
at the aft end of the skin stiffeners.
NOTE
Be careful while
undamaged
cutting
the
bonding
material to
prevent damage to the honeycomb stiffeners
the
skin.
h.
Drill out the rivets that attach the skin to the spar and remove all
i.
Remove the skin from the elevator.
j.
If the upper skin is to be
4-24
on
replaced,
attaching
drill out the rivets in the tab actuator rod
sc rews
fairing
from the skin.
and
remove
the
fairing.
E16
BEECH BARON 55 AN D 58 SHOP MAN UAL
k.
Rem ove the stiffeners from the
skin
new
as
damaged
skin and
necessary to match the old skin. Do not drill the
I
the skin to the
secure
trailing edge
CAUTION
cnu-now
replacement
skin. Trim and drill the
rivet holes.
I
throughout the assembly procedure. The replacement skin
end. The
must fit so that the trailing edge is perfectly straight from the inboard end to the outboard
centerline of the trailing edge must be on the same centerline as the hinges (see Figure 4-10).
Extreme caution must be exercised
i.
Paint the inside of the
new
skin and the
attaching
surfaces of the elevator structure with epoxy
primer.
DO NOT
PRIMEAR EAS TO BEBONDED.
m.
Remove all rivet butts, metal
shavings
and burrs from the elevator structure and skin.
NOTE
co rrect s ize
Use M S20470 B rivets of the
and
length
to secure the skin to the
e levato r, exce
pt
as
noted.
n.
Install the tab actuator rod
o.
Position the
new
skin
on
fairing (upper
skin
only).
the elevator structure and hold in
Rivet the skin to the elevator spar and ribs
p.
loose.
place
working from the
with Cleco fasteners.
center out to each end. Leave the
trailing edge
NOTE
r e levato r
a re i n stal I ed at the forward tab actu ato r rod opening on n ewe
the
to
skin
the
to
secure
and
spar in
size
of
correct
the
rivets
length
MS20470AD
Use
assemblies.
45-61 0005-1 4 channels
the
area
of the channel.
q.
Rivet the skin to the
r.
If both skins
are
hinge
to be
bracket.
replaced, repeat
the
preceding procedure
on
the
remaining
skin.
PR1440
apply PR890 (P/N of Coast Proseal Company, Los Angeles California) or
skin. Apply the
(P/N of P ro d ucts Research, Bu rbank California) bonding cement to the bonding strips on the new
uf acturer.
bondi ng cement just bef ore riveting the trailing edge and allow curing time as specif led by the sealant man
s.
Clean the
bonding strips,
and
CAUTION I
I CAUTIDN
Do not
to
t.
Insert
use
only one
a new
too much cement
side of the bond
it
can
affect the elevator balance.
Apply the
cement 1/8-inch thick
area.
96-610006-15 inboard
the fixed elevator tab between
E16
as
trailing edge spacer,
the trailing edge skins.
a new
96-610006-35 outboard
trailing edge spacer and
4-25
B E ECH BARON 55 AND 58 SHOP MAN UAL
Use
u.
a
clamping
device to
clamp
the
bonding
area
of the elevator. Refer to
Figure
4-10.
NOTE
clamping
device must be
suitable
clamping
device to hold the
v.
Use
w.
Drill rivet holes in the
x.
Rivet the
trailing edge.
y.
Install all
screws
z.
Pai nt the elevate r.
aa.
Balance the elevator.
a
tightened just enough
The
and
ab. Install the elevator
on
trailing edge using
trailing edge
the
same
to hold the bonded area
of the skins
spacing
as was
together for drilling
used
on
together.
and
riveting.
the old skin. Use
a
No. 40 drill bit.
attaching hardware removed during disassembly.
(See
the
BALANCING THE EL EVATO R)
airplane.
RIGGING THE EL EVA TOR CONTROL S YS TEM
(TC-1 AND AFTER; TE-I AND AFTER; TH-I THRU TH-1388, TH- 1390 THRU TH- 1395)
FIG URE 4- 1 1
NOTE
Beech
recom me nds
the
use
of the elevator travel gage shown in the GENE RAL IN FORMATION
section of this manual. Locate the travel gage at station 35.75.
the upper elevator stop bolt so that the centerline of the bottom cable attachment hole in the elevator
bellcrank is 0.70 to 0.80 inch from the aft bulkhead.
a.
Adjust
C.CLAMP OR
.E QUIVAL ENT
TOOL
HINGE POINT
CENTER LINE
BOND AREA
UPPER SKIN
EXTRUSION OR SOME
O TH E R RIG ID MATER)A L
TO CLAMP BONDED AREA
LOWER SKIN
TRAILING EDGE
55-135-3
Elevator Skin
(TC-547
and After; TE-1
Replacement
and
Fig ure
4-26
After; TH-1
and
Afte r)
4-1 0
El 6
BEECH BARON 55 AND 58 SHOP MAN UAL
of the elevator
rods to obtain 14" to 16" of down travel.
push-pull
b.
Adjust
the
c.
Adjust
the lower stop bolt in the elevator bellcrank to obtain 29" to 31" of up travel.
d.
Rig
length
the cable tension
as
shown in
Figure
Adjust the
4-1 1.
stop before the control column is in the full forward
cable
so
that the elevator bellcrank contacts its down-
position.
NOTE
the top and bottom cables with the
the stop and the downsprings connected.
Tens io mete r read i n gs
position against
e.
be taken
m ust
With the elevator bellcrank
against
on
its upstep,
adj ust
e levato r
the control colu mn stop to obtain
a
i n th e down
clearance of 0.06 to
0.12 inch.
f.
Check elevator travel.
WARNING
IWARNING)
Check the elevators for correct direction of movement. When the control wheel is moved
forward, the elevators must move down. When the control wheel is moved aft, the e levato rs
mu st move
g.
up.
Check the elevator
downspring
loads
as
described in the
following procedure.
ELEVA TOR DOWNSPRING LOADS
With the
sure
the
downsprings connected, the loads in the elevator control system must be
loads in a draft-free area using a push-pull scale on the control wheel.
within the limits
given
below. Mea-
ForTC-l and After:
(down elevator),
24 to 28
pounds
breakout
23 to 25
pounds
breakout at O" elevator
10 to 12
pounds
at 30" up elevator
(0.06
(neutral),
inch off
stop).
For TE-1 and After:
21 to 24
pounds breakout (down
22 to 24
pounds breakout
20 to 21
pounds
For TH-1 thru
at O" elevator
at 30" up elevator
TH-1388,
(0.06
r),
(neutral),
inch off
stop).
TH-1390 thru TH-1395:
through
32 to 35
pounds moving
the control wheel aft
19 to 33
pounds moving
the control wheel forward
0 to 14
El 6
e levato
pounds
difference between
ne ut ral
through
f rom fu II d ow n elevator,
neutral from full up elevator,
readings.
4-27
BEECH BARON 55 AN D 58 SHOP MAN UAL
RIGGING THE ELEVA TOR CONTROL SYSTEM (TH-1389, TH- 1396 AND AFTER)
FIG URE 4- 12
WARNING
IWARNING
When
replacing
or
installing
control
components, observe the color coding
to coded parts of a different color.
on
cables, bellcranks and other control system
all parts. Do not connect coded parts of one color
NOTE
Beech reco m me nd s th e use of the elevate r trave I gage shown in the G E N E RA L I N FO R M AT I O N
section of this manual. Locate the travel gage at station 35.75.
To
to
position the elevator
Figure 4-13.
in neutral,
a
tool
can
be fabricated from 5/16-inch-diameter steel rod. Refer
Adj ust th e upper elevator stop bolt so that the centerline of the bottom cable attachment hole in the elevator
bellcrank is 0.70 to 0.80 inch from the aft bulkhead.
a.
b.
Adjust
the
c.
Adjust
the lower stop bolt in the elevator bellcrank to obtain 29" to 31" of up travel.
d.
Disconnect the elevator downsprings.
length
of the elevator
push-pull
rods to obtain 14" to 16" of down travel.
Set the elevator controls in neutral. To obtain neutral, insert the short end of the fabricated tool in the control
hanger. Refer to Figure 4-13. Move the control wheel aft and insert the other end of the tool into the control
shaft and torque tube.
e.
column
f.
Rig
cab le te ns i o n
as
shown in
Figure
4-11.
NOTE
Tensiometer
readings
must be taken on the upper and lower elevator cables with the
downsprings
disconnected.
g.
Connect the elevator
h.
Check elevator travel.
downsprings.
WARNING
WARNING)
Check the elevators for correct direction of movement. When the control wh ee I i s moved
the elevators must move down. When the control wheel is moved aft, the elevators
forward,
must move up.
i.
Check the loads in the elevator control system in a draft free area using a push-pull scale on the control wheel.
control wheel aft from full down elevator, the load through neutral must be 39 to 43 pounds. Pushing the
control wheel forward from full up elevator, the load through neutral must be 23 to 27 pounds. The difference be-
Pulling the
tween the two
4-28
readings
must be 13 to 19
pounds.
E16
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ELEV.
ELEV.
BELLCRANK
STOPS
DOWN
NOSE
DOWN
NOSE
DETAIL
ELEVATOR
UP
UP
1~?j
C
CONTROL
COLUMN
STOP
D
ELEV.
F.S.
UP
tLEV.
O
DOWN
ELEVATOR
TAB
F.S.
STOPS
F.S.
IO
ELEVATOR-DOWN
CABLE
C
A
~Y
8_
I
F.S.
F.S.
NOSE
NOSE
1 85.00
ELEVATOR-UP
DETAIL
170.000
F.S.
E
F.S.
D
F.S.
233.50
118.50
j
10
20
UP
ELEV.
NOSE
cn
o
DOWN
30
40
50
60
70
80
90
100
110
90
100
110
50
DOWN
D
NOSE
u,
UP
40
SLE’!RTOR
o
r
30
P.
o
cn
iiivRTP~
iAB
30
E45
w
20
IT
CC~IIII
rll~l-.
I
50
60
70
TEMPERATURE
B55
SpPER
CABLES
80
90
MINIMUM
rrrnm
10
MAXIl?t)M,
100
~’;ldwik ELEV,4T,O~
110
20
DETAIL
B
F.s.
CABLE
118.5
-"F
SERIALS
CABLE
;;r;sW.E~
F.S.
40
58
:MIr~
-´•IATOF1 TAB
ELEVATOR
30
~OWFP_
OABL~
20
H
t~
CABLE
20
40
z
247 .830
140.00
ELEV.
O
257.606
30
I
50
a~
262.90
151 .00
UP
DOWN
DETAIL
F. S.
272.000
I 12.000
30
40
50
60
70
80
F"
TEMPERATURE
E55 AND 58 SERIALS
M04B
991183AA.AI
Rigging the Elevator Control System
(TC-1 and After; TE-I and After; TH-1 thru
E16
4-29
BEECH BARON 55 AND 58 SHOP MAN UAL
THIS PAGE INTENTIONALLY LEFT BLANK
4-30
E16
Ral~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
ELEV. UP
I
I~
I
ELN. DOWN
3
NOSE DOWN
~NOSE
IIRNDl
DETAIL
UP
C
F.S. 272.000
it
D
\-5.5.
i/
26290
F.S. 257.606
C
A
DETAIL A
F.S. 247.830
~Y
B
~c‘rJ
ELEV. DOWN
F.$.
~CSELEV.
nl II
UP
170.000
DETAIL
F.S. 151.00
d~ F.S.;~8.50
F.S. 233.50
TEMP~ATURE CABLE TENSION GRAPH
b
KFC 200 AUTOPILOT ELRIATOA AND BfVATOR TAB CABLES
ELEV.UP
cn
ELEV. DOWN
3
B
NOSE WWN
z
ELRI.UP7
30
20
9
NOSE UF
/d
IlFWDs
NOSE UP
30
40
50
NOSE DOWN
60
70
90
so
100
Ilo
TEMPERATURE S
F.S. 118.50
~S. 112.000
TEMPERATURE CABLE TENSION GRAPH
MOOB 58aRlATOR CABLES
TEMPERATUF~E CABLE TENSION GRAPH
(940
H-14 AND 59-3 AUTOPILOT ELEVATOR AND ELEVATOR TAB CABLES
DETAIL
B
u,
o
TEMPERA’I’URE CABLE TENSION GRAPH
ALL EtEVATOR TAB CABLES EXCEPT
AUTOPILOf
g
30
os
z
~2
~nJ3A‘
20
n
z
~ao
B
z
;ioR_
o
o
~L
220
14
~Ev
L,.
8
T
eAB~F::
F,,
30
40
50
60
70
80
90
100
110
TEMPERATURE "F
30
40
50
60
70
TEMPERATUF(E "F
80
90
100
110
60
70
TEMPERATURE
so
q
90
100
110
NOTE: RIG AUTOPILOT CABLES AmR CONTROL SYSTEM CABLES ARE RIGGED.
sslszs
Rigging the Elevator Control System
(TH-1389, TH-1396 and After)
Figure 4-12
E16
4-31
BEECH BARON 55 AND 58 SHOP MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
4-32
E16
B E EC H BARON 55 AND 58 SHOP MAN UAL
EL E VA TOR TRIM TAB RIGGING
NOTE
Airplane serials TO-1 through TC-1 1 94 are equipped with e levato r t ri m tabs which are cambered
only on the bottom surface. Airplane serials TC-1195 and after, TE-1 and after and TH-1 and after
use u ncambe red
tri m tabs.
gage shown in the GENE RAL
INFORMATION section of this manual. Locate the travel gage at station 35.75.
Seech
To
recommends the
after,
serials TC-1437 and after, TE-860 and after and THbe fabricated from 5/16-inch-diameter steel rod as shown in Figure 4-13.
elevators in neutral
position the
223 and
of the elevator trim tab travel
use
a
tool
can
airplane
on
on airplane serials prior to TC-1437, TE-860 and TH-223, insert
in the control shaft torque tube and control column hanger.
holes
matching
locking pi
To obtain neutral on later models, insert the short end of the fabricated tool into the control column hanger. Refer to
4-13. Move the control column aft and insert the other end of the tool into the control shaft and torque tube.
Set the elevators in
a.
n e ut mi.
the control column
n
To
o btai n
neutral
i nto the
Figure
b.
Set the elevator trim tab control to 23"
c.
Adjust
d.
Set the tab at 23" down and connect the
e.
Install the chain
Tighten
f.
of
the tab actuator
on
so
nose
up.
that the actuator rod extends for two-thirds of its total travel.
the actuator sprocket
pushrod
so
to the actuator.
that the three links
on
the bottom of the
sprocket are
left
unengaged.
the cables.
Rig the tab cable tension as shown
the two cables must be equal within
in
2
Figures 4-1 1
pounds.
Check the elevator trim tab travel and
g.
24" deflection below the elevate r.
Safety
wire the turnbuckles and stops.
i.
Use
push-pull
a
scale to check the force
over
the
following
4-12. Where the cable divides into two
adjust the tab cable stops to
h.
the force must not be
or
required
to
move
cables, the tensions
obtain 9" to 1 1" deflection above, and 22" to
the tab cable system.
Pulling
in line with the cable,
limits:
TC-1 and After
20 Pounds
TE-I and Af te r
20 Pounds
TH-1 thru TH-1 388, TH-1 390 thru TH-I 395
2 0 Po u n d s
TH-1389, TH-1396 and After
20 Pounds
WARNING
IWbRNING)
the elevator and elevator trim tab control system, check for correct movement
of the control surfaces with respect to the movement of the controls. When the elevator trim
tab control is moved toward the NOSE DOWN position, the elevator trim tab should move
After
rigging
U P.
El 6
4-33
BEECH BARON 55 AND 58 SHOP MANUAL
REPLACING THE EL E VA TOR TRIM TA B INDICA TOR CABLE
(TC- 1 A ND A FTER,. TE- I A ND A FTER; TH- I THRU TH- 1 388, TH- 1 390 THRU TH- 1 395)
NGURE 4- 14
NOTE
On the later TH serials the elevator trim tab indicator is driven
a.
The elevator trim tab control system must be
b.
Install the indicator cable
of the cable out
c.
through
through
directly by the
correctly rigged and the
the head of the cotter
pin
on
tab control wheel.
elevator control in neutral.
the side of the indicator drum.
Bring
both ends
the hole in the indicator drum.
With the indicator set
a
O"
(neutral),
both ends of the cable must be
equal
in
length.
each end of the cable around the drum one full tum in opposite directions. The end that wraps to the right
clockwise
around the drum, and the end that wraps to the left wraps counterclockwise around the drum, as
wraps
viewed from the left side.
d.
Wrap
e.
Route both ends of the cable
f.
With the indicator still at O"
clockwise)
over
the idler
(neutral),
pulleys
take the cable
down to the shaft of the tab control wheel.
coming off the top of the
indicator drum
(wrapped
counter-
down to the forward side of the control wheel shaft to the left of the hole.
FABRICATE FROM 5/16 INCH DIAMETER STEEL ROD
AIRPLANE SERIAL NO.
DIMENSION A
TC-1 431 AND AFTER
TE-860 AND AFTER
TH-223 THROUGH
TH-1 388
1.75 INCHES
TH-1390 THROUGH
TH-1 395
TH-1 389
TH-1396 AND AFTER
2.50 INCH ES
C96NeutralRig
Figure 4-13
Elevator
4-34
Pin
E16
BEECH BARON 55 AND 58 SHOP MANUAL
g. Wrap the cable counterclockwise las viewed from the left) arou nd the shaft toward the hole three fu II tu ms. Insert
the cable through the holes and wrap the excess cable clockwise around the shaft.
h.
Take the cable
coming off the bottom of the indicator
right of the hole.
drum
(wrapped clockwise)
down to the aft side of the
con-
trol wheel shaft to the
Wrap
the cable clockwise
las viewed from
cable th ro u g h the holes and wrap the
excess
j.
Twist the two cable ends
k.
Check the tab control and dial to be
i.
Check the tab travel and direction of
together
the
left)
around the
and solder with rosin
sure
s h aft
towa rd th e hole three full turns. Insert the
cable counterclockwise around the shaft.
that it
moves
move ment
to be
solder.
core
from
freely
sure
that it
one
stop
to the other.
corresponds
to the movement of the control
and ind icato r.
EL EVA TOR TRIM TA B A CTUA TOR REMO VAL
a.
Remove the
access
panel
near
the
trailing edge
of the ho rite ntal stabilizer to
gain
access
to the elevator trim
tab actu ato r.
b.
Detach the tail cone, disconnect the tail
c.
Remove the
access
panel
on
d.
Remove the
access
panel
near
navigation light
the left hand side of the
the
leading edge
wire and
remove
fuselage just
the tail
cone.
forward of the horizo ntal stabi lize r.
of the horizontal stabilizer to
gain
access
to the elevator trim
tab actu ato r sp rocket.
outlined in Section 4 of this
Manu al under the
e.
Remove the elevator
f.
Disconnect the elevator trim tab cables at the turnbuckles in the aft
as
tab cables to prevent them from
unwinding
Shop
heading ELEVATOR REMOVAL.
fuselage. Secure
the forward elevator trim
at the universal.
CAUTION
I cnvnoEIl
Do not
damage the
g.
Remove the chain and cable
h.
Remove the hardware
cables. Use
assembly from
attaching
a
material such
as
phenolic
to
the elevator trim tab actuator
protect the cables.
sprocket.
the elevator trim tab actuator to the horizontal stabilizer. Remove the actuator
fro m the ai rplane.
NOTE
If the actuator is to be
reinstalled, identify with
a
tag
to ensure proper movement of the elevator tabs
upon reinstallation of the actuators.
E16
4-35
BEECH BARON 55 AND 58 SHOP MAN UAL
COTTER PIN
1
1
WRAP ONE FULL
TURN IN BOTH
DIRECTIONS
111/1
11I1I
11
INDICATOR DRUM
(SHEAVE)
ROTATED
90"
DETAIL
A
O
IDLER
PULLEY
TIE AND
SOLDER
7
~A
1I
INDICATOR
DRUM (SHEAVE)
r-
II I I
I
~I
)1
nB
W/
TRIM TAB CONTROL
WHEEL SHAFT
ROTATED 90~
WRAP 3 FULL TURNS
DETAIL
TRIM
CONTROL
WHEEL
B
~1529
Elevator Trim Tab Indicator Cable
(TC-1
and After; TE-1 and
After; TH-1 thru TH-1338, TH-1390 thru TH-1395)
Figure
4-36
4-14
El 6
BE ECH BARON 55 AND 58 SHOP MANUAL
EL E VA TOR TRIM TA B A C TUA TOR INS TALLA TION
WARNING I
IWARNINO
To
ensure
installed
on
right-hand
proper movement of the trim tabs, make sure that the left-hand actuator is
the left-hand horizontal stabilizer and the right-hand actuator is installed on the
h o rite nta I sta b i I izer.
The trim tab actuator that will be installed
threads
its actuator
on
on
the left-hand horizontal
The trim tab actuator that will be installed
assembly (2). Refer to figure 4-15.
hand horizontal stabilizer, shall
have threads
on
the actuator
counterclockwise when screwed into the nut assembly
The elevator trim tab actuators must not be
horizontal stabilizers when
they
are
(2).
coding
probability
of
screw
figure
on
(4)
the
right
that rotate
4-15.
between the
right and
left
the actuators, reverses the
inadvertent nose-down trim condition
and nose-up trim would actually result in an
that could res u it in an uncontrollable airplane att itu de
to reduce the
Refer to
interchanged
Reversing
reinstalled.
direction,
color
stabilizer, shall have
that will rotate clockwise when screwed into the nut
(4)
screw
Ref er to elevator trim tab actuator
unintentionally switching
the actuators upon
installation.
a.
Position the elevator trim tab actuator in the horizontal stabilizer and install the
b.
Position the chain and cable
within
0.20 inch at the
assembly
sprocket
the actuator
on
sprocket
hardware.
that the ends of the chain
a re e q u i d i sta nt
centerline.
outlined in Section 4 of this
Manual under the
c.
Install the elevator
d.
Connect the elevator trim tab cables to the turnbuckles in the aft
e.
Remove material used to protect the cables.
f.
Rig
as
so
attaching
the elevator trim tab control system
TO R TR IM TAB RIGGING.
as
Shop
heading ELEVATOR INSTALLATION.
fuselage.
outlined in Section 4 of this
Shop
Manual under the
heading ELEVA-
NOIE
After
rigg ing
the
co nt ro I s u rf aces
e levator an d e levator
with
re s
pect
tri m tab control system, check for correct movement of the
e levato r tri m tab control
to the moveme nt of the co nt rot s. Wh e n t h e
wheel is moved toward the NOSE DOWN
position,
g.
Install the
access
panel,
located
near
the lead i n g
h.
Installthe
access
panel,
located
near
the
1
i.
E16
Install the
access
Connect the tail
panel
on
edge
trailing edge
the elevator trim tab should
wire and install the tail
UP.
of the h o ri to nta I stab i I i ze r.
on
the ho rite ntal stabilize r.
the left-hand side of the fu selage,
navigation light
move
j u st
fo Mward of the h o rizontal stabi lize r.
cone.
4-37
BE EC H BARON 55 AND 58 SHOP MAN UAL
EL E VA TOR TRIM TA B A CTUA TOR COL OR CODING
Elevator trim tab actuators should be color coded with LH blue and RH black. Color coding of the elevater trim tab
of
actuators can be accomplished with the actuators installed or before installation. This will reduce the prob ability
unintentionally switchingthe actuators. Use Beech Mandatory Service Bulletin No. 2399 for painting instructions on
how to color code elevate r trim tab actu ators.
wn RNING)
I WARNING
Do not in stall
on a
a
blue-coded actuator
on a
black-coded stabilizer
or a
black-coded actuator
blu e-cod ed stabilizer.
ELEVA TOR TRIM TAB A CTUA TOR DISA SSEMBL Y
(TC- 1 THRU TC- 1143; TE- I THRU TE-61 7)
FIG URE 4- 1 5
NOTE
Refer to Beech Se rvice In structio ns No. 061 0-1 52, Revision II, for modification of the
e levato r
t ri m
tab in stallatio n.
ring (1) from the
a.
Remove the snap
b.
Remove the actuator
c.
Drill out the rivets
bearing (7)
and the
screw
(4)
actuator
from the nut
housing (11),
and
pull
the nut
assembly (2)
out of the
housing.
assembly.
(12 and 13), and remove the spacer (5)
bushing (8) can now be removed from the
and the actuator rod end
(6)
from the
screw.
The
screw.
NOTE
and spacer (5) were replaced with a shoulder
TC-1073 through TC-1143, TE-521,TE-528
serials
TC-1071,
airplane
Refer
to
TE-617.
Figure 4-15 insert.
through
and
13)
d.
Remove the check nut
(9),
e.
Remove the
O-ring (14)
from the
f.
Remove the
bearing (3)
from the nut assembly.
The rivets
(12
and
screw
out the
pin, washer, nut and rivet at
through TE-538 and TE-543
adjusting bushing (10) using
a
spanner wrench.
adjusting bushing.
ELEVA TOR TRIM TAB A C TUA TOR CLEANING AND L UBRICA TION
(TC- I THRU TC- 1143; TE- I THRU TE-61 7)
NOTE
Refer to Beech Service Instructions No. 0610-152, Revision II, for modification of the elevator trim
tab installation.
Clean all parts in solvent
distortion.
a.
4-38
(1 5,
Consu mable Materials Chart, Section
2)
and
inspect
for cracks, corrosion and
E16
BEECH BARON 55 AND 58 SHOP MANUAL
Replace any parts showing evidence of
able Materials Chart Section 2).
b.
Lubricate the
c.
O-ring
wear.
with Silicone Co m pou nd
Lubricate the
(57,
screw
threads with
lubricating
Co ns u mable M ate ri a is C h a rt, S e cti o n
(TC- I
EL E VA TOR TRIM TA B A C TUA TOR A SSEMBL Y
g rease
(1
1
Co ns u m-
2).
THRU TC- 1 1 43; TE- 1 THRU TE-6 1 7)
FIG URE 4- 15
a.
Install the
bearing (3)
b.
Install the
bushing (8)
c.
Install the actuator rod end
on
the nut
and the
assembly (2).
bearing (7)
(6)
on
the
on
screw
the actuator
using
screw
the spacer
(4).
and
(5)
rivets
new
(12
and
13).
NOTE
(12 and 13) and spacer (5) were replaced with a shoulder
serials
TC-1071, TC-1073 through TC-1143, TE-521, TE-528
airplane
Refer to Figure 4-15 insert.
TE-617.
through
The rivets
d.
Install the actuator
into the nut
screw
pin, washer, nut and rivet at
through TE-538 and TE-543
assembly.
WARNING
IwnRNINal
The trim tab actuator that will be installed
threads
its actuator
on
(4)
screw
on
the left-hand horizontal
stabilizer, shall have
that will rotate clockwise when screwed into the nut
assembly (2). The trim tab actuator that will be installed on the right-hand horizontal
stabilizer, shall have threads on the actuator screw (4) that rotate cou nterc loc kwise when
screwed into the nut assembly (2).
into the actuator
housing (11).
e.
Push the nut
f.
Install the snap
g.
Install
O-ring (14)
h.
Use
is
no more
spanner wrench to install the adjusting bushing (10) into the housing until end play of the nut assembly´•
than 0.005 inch. The nut assembly must be free to rotate with no more than 1 5 inch-pounds of toro ue
to the
in the
ring (1)
in
housing.
bushing (10).
shaft, with
no
Install the check nut
(9)
applied
i.
a
assembly
binding.
on
the
If the end
play
cannot be reduced to within
limits, replace the actuator.
adjusting bushing.
EL E VA TOR TRIM TAB A C TUA TOR DISA SSEMBL Y
(TC- 1 144 AND AFTER;
TE- 6 18 A ND A FTER; TH- 1 A ND
AFTER)
FIG URE 4- 1 6
(1)
a.
Rem ove the
bearing
b.
Remove the
retaining ring (2) from
c.
Remove the check nut
d.
Rem ove the nut
E16
cap
(8)
from the
housing (5j.
the actuator
and the threaded
assembly (6)
bushing (7)
and the actuator
pull
the collar
from the
housing.
and
housing
screw
(4)
from the
(3)
out of the
housing.
housing.
4-39
BEECH BARON 55 AND 58 SHOP MANUAL
EL EVA TOR TRIM TAB A CTUA TOR CLEA NING A ND L UBRICA TION
(TC- 1 144
AND AFTER; TE-6 1 8 AND A FTER; TH- 1 A ND A FTER)
NOTE
Refer to Beech S e Ni ce I nst ru ct io n s No. 061 0-1 52, Revisi o n I I, fo r modificatio n of the
e levato r
t rim
tab i nstallation.
(1 5,
b.
Replace
evidence of
c.
Lubricate all parts with
any parts
showing
2)
Consu mable Materials Chart, Section
Clean all parts with solvent
distortion.
a.
and
inspect
for cracks, corrosion and
wear.
lubricating grease (11, Consumable Materials Chart, Section 2).
EL E VA TOR TRIM TA B A CTUA TOR A SSEMBL Y
TE-6 1 8 A ND A FTER; TH- I A ND A FTER)
(TC- 1 144 AND AFTER;
FIG URE 4- 1 6
a.
Install the actuator
screw
(4)
into the nut
assembly (6).
WARNING
IWARNINCI(
the left-hand horizontal stabilizer, shall have threads
on its actuator screw (4) that rotate clockwise when screwed into the nut assembly (6). The
trim tab actuator to be installed on the right-hand horizontal stabilizer, shall have threads on
The trim tab actuator to be installed
the actuator
screw
(4) that rotate
on
counterclockwise when screwed into the nut assembly
1.
SHOULDER
1
PIN
Airplane
serials iC-1071,
TC-1 073
through TC-1143,
TE-521, TE´•528 through
TE-538 and TE-543 through
TE-617
3.
4. Actuator Screw
RIVET
5. Spacer
6. Actuator Rod End
7. Bearing
6~5
8.
a~e NUT
10.
11.
12.
4
13.
!2
10
Bushing
9. Check Nut
14
9
Snap Ring
Assembly
Bearing
2. Nut
WASHER
2
(6),
14.
13
Adjusting Bushing
Housing
Rivet (AN470AD-3)
Rivet ~AN470A03)
O-ring
s
s
7
1
5
6
55-164´•10
Elevator Trim Tab Actuator
(TC-1
thru TC-1 1
43; TE-1 th ru TE-61 7)
Figure
4-40
4-15
616
BEECH BARON 55 AND 58 SHOP MANUAL
assembly
b.
Install the nut
c.
Install the collar
housing (5).
and the retainer
ring (2)
in the
housing.
spanner wrench to install the threaded bushing (7) into the housing until total end play of the nut assembly
than 0.010 inch. The nut must be free to rotate and operate smoothly through its full travel. if end play
d.
Use
is
no more
a
(3)
into the
cannot be reduced to within
e.
Install the check nut
f.
Install the
(8)
limits, replace the
on
bearing cap (1)
the threaded
the
on
actuator.
bushing.
housing.
CHECKING EL E VA TOR TRIM TAB FREE PLA Y
FIGURE 4-1 7
Visually inspect
of the
actuating
0) or equivalent, a d ial i nd icato r, and a push-pull scale for applying
making the inspection for tab free play. Refer to Figure 4-17.
accurate
the elevator trim tab for
damage, security of hinge attach points, and
checking the free play of the tab.
for
tightness
system. Inconsistencies must be corrected before
A check fixtu re
loading
a.
(P/N
45-1 35030-9/81
to the tab are
required
for
lock the control surfaces to prevent movement of the elevators. Set the elevator trim tab in neutral.
Securely
b.
dial indicator check fixture
tab
TH-1 and
Use shot bags to hold the
hinge line (TE-1 and After;
edge of the elevator tab.
c.
Apply
a
small
piece
of
After)
or
so
that the
point of the dial indicator is 4.0 inches aft of the
hinge line (TC-1 and After) on the outboard
3.3 inches aft of the tab
masking tape (for paint protection) 4.5 inches aft of the tab hinge line
point of pressure against the tab by the push-pull scale.
and
along
the
cen-
terline of the tab actuator. This is the
piece of masking tape in the corresponding location
d.
Apply
e.
Set the dial indicator at
f.
With the
g.
Release half of the load to obtain
h.
On the
i.
Release half of the load to obtain
j.
8 nte r th e
another
zero.
push-pull scale
masking tape
reco rd ed
by
on
on
Do not reset the dial indicator
the
masking tape, apply
a
readings
on a
2 and record
a
Subtract A from 28 and record
3.
Multiply
4.
Subtract C from 2D and record
by
2 and record
pound
the
checking procedure.
downward load. Record the dial
a
pound upward
3.0
pound upward
the dial
as
as
reading
a
as
A.
8.
load. Record the dial
load. Record the dial
proceed
reading
reading
reading
as
C.
D.
fo I I ows:
28.
2.
D
apply
copy of Chart 4-2 and
Multiply
a
1.5
3.0
the bottom surface of the tab.
pound downward load. Record
the bottom surface,
1.
B
1.5
a
during
on
as
as
X.
2D.
as
Y.
N OiE
Xand Ycan be
5.
816
Add X and Y and record
as
negative
numbers.
E.
4-41
BE ECH BARON 55 AND 58 SHOP MAN UAL
OO/A
CHECK
NUT
2
BUSHING
3
NUT
4
HOUSING
8
ASSEMBLY
5
ACTUATOR
6
COLLAR
7
RETAINER
8
CAP
SCREW
10
RING
DETAIL
A
C95TH2780935 C
Elevator Trim Tab Actuator
(TC-I 144
4-42
and After; TE-618 and After; TH-1
Figure 4-16
and
Afte r)
Et6
BEECH BARON 55 AND 58 SHOP MAN UAL
k.
If the free
play
is
over
the maximum
specified in Chart 4-2, inspect
replaced.
to determine the cause. All worn
parts
I.
the other elevator trim tab.
Repeat steps
b
through
k
on
all components of the tab actuator system
must be
C HA RT 4-2
E LE VATO R TA B FREE P LAY LIMITS
1.&POUND
3-POUND
READING
READING
28
-A
=X
2D
C
=Y
+Y
=E
X
E
0.084 inch maximum
(TE-I
and
After; TH-1 and Afte r)
E
0.069 inch maximum
(TC-1
and
After)
EL E VA TOR TRIM TA B HORN REPA IR
NOTE
Elevators must be removed from the
p roced u res descri bed be low
are
airplane
performed.
and checked for static balance after the
repair
FOR TAB HORNS WITH BRAZED IN BUSHINGS
Carefully grind
a.
or
spot face the brazed-in bushing flush with the sides of the tab horn.
NOTE
Maintain the
b.
Drill and
ream
the
bushing
existing
centerline
hole to
an
as
nearly perpendicular
as
possible
to trim tab tu be centerline.
inside diameter of 0.4995/0.5010-inch.
clean rag dampened with solvent (19, Consumable Materials Chart, Section
hole in the tab horn, the area around the hole and a new P/N 96-610026-1 bushing.
c.
Using
d.
Scuff sand the contact surfaces of the
step
e.
f.
a
and the tab horn and clean the
area
thoroughly
as
clean the
specified
in
c.
Wipe
off the parts with
a
clean rag before the solvent evaporates.
Apply a thin coat of adhesive (37,
bushing and the tab horn.
El 6
bushing
2), thoroughly
Consumable Materials Chart, Section
2)
to the contact surfaces of both the
4-43
BEECH BARON 55 AND 58 SHOP MAN UAL
9
12
to
678
13
11
5
i
.e IN
1-;
--i
.5 IN
P
’-1´•r--------------------------1~
’f
1
5/8-1)
rAP
I
1.25 IN’
TYP,
O
C
4
2.9 IN
1
i
I
.25 IN
1.AtA
f-I
TAB
14
/I‘/tls"
1.30 1N
ITEM
QUANT.
i
DESCRIPTION
-rr:
t
NO.
.68 1N
1
6 aluminum or
equiv.
1
2
3/4
2
2
1
3
1
1/2
4
1
C81Q Indicator"
5
1
3/4
6
1
1/4 Dia. x2 corrosion
res.
stl.
7
1
1/4 Die. xlcorrosion
res.
stl.
8
1
1/4-28 nut
9
1
3/8
10
1
3/8 x2x10 rubber
11
1
1/4
x
2
12
2
1/2
x
13
13
2
KNB13 Keensert
14
2
118
"P/N of Federal Products
x
x
x
1 3/8
x
x
x
x
x
7 1/2
2 1/2
5
1
x
x
x
1 3/4 aluminum
x
x
10 aluminum
14 aluminum
or
equiv.
equiv.
or
equiv.
or
-r--H
1.6 IN
.311N
10 rubber
10 corrosion
x
3 VLIER
or
R. I.
stl.
screw
_I
SE CTION
tap 1/2- 13
3/4 rubber
Corp., Providence,
res.
Torque
I
AA
THIS GROOVE TO BE A SNUG FIT
TO THE SCREW BRACK ET ON
THE DIAL INDICA TOR
loo-lls-a
Fabricating Clamp for Tab Deflection
Figure 4-17
4-44
E16
B E EC H BARON 55 AND 58 SHOP MAN UAL
Join the hem,
g.
bushing
clamp together until the adhesive
and
completely (approximately
has cured
24
hours).
NOTE
When
the horn and
clamping
h.
Lubricate the
2)
and install the
new
104-524056-3
grip bushing in the
bushing together,
grip bushing
use care
not to squeeze out all of the adhesive.
lubricating grease (11,
bushing.
with
Consumable Materials Chart, Section
96-610026-1 tab horn
i.
Install the trim tab and lubricate all
tion
2).
pivotal points with lubricating
I
(11,
grease
Consumable Materials Chart, Sec-
NOTE
If the rod end
When
on
the
connecting
pushrod assembly
the tab
is worn, the
pushrod assembly
pushrod assembly
to the tab ho rn,
should be
replaced.
tighten the castellated nut against the
key. The grip bushing must be
rod end and turn the nut to the next castellation to install the cotter
secure
within the
yoke,
the rod end should not rotate.
FOR TA B HORNS OF O.1~S-INCH-THICK FLAT STEEL SHEET AND N O BUSHINGS
NOTE
Maintain the
a.
Drill and
b.
Using
a
ream
bushing centerline
the
existing
as
nearly perpendicular
hole in the tab horn to
an
to the trim tab tube centerline as
possible.
inside diameter of 0.3745/0.3760 inch.
clean rag dampened with solvent (19, Consumable Materials Chart, Section
area around the hole and a P/N 96-610026-3 bushing.
2),
clean the hole in the
tab horn, the
c.
Scuff sand the contact surfaces of the
bushing and
the tab horn, and clean the
area
thoroughly
as
specified
in
step b.
d.
Wipe
off the parts
again
with
a
clean rag before the solvent evaporates.
Apply a thin coat of adhesive (37,
bushing and the tab horn.
e.
i.
bushing and clamp together (use
completely (approximately 24 hours).
Join the tab horn and
adhesive has cured
g.
Consumable Materials Chart, Section
Install the trim tab with
a new
P/N 96-526021-1 rod
care
assembly
2)
to the contact surfaces of both the
not to squeeze out all of the
and
a new
adhesive)
until the
NAS464P4-8M bolt at the tab horn end.
NOTE
necting the tab pushrod to the tab horn, the rod end
ag ai n st th e bushing in the tab ho m. (Tu m i ng the nut on the
castellation should accomplish this.)
When
h.
E16
con
Lubricate all
pivotal points
with grease
(11,
must be free to
move
Consumable Materials Chart, Section
binding
plus one
without
bolt to contact the rod end
2).
4-45
BE ECH BARON 55 AND 58 SHOP MANUAL
FOR TA B H O R NS OF 0.091-INCH-THICK ALUMINUM WITH APR ESS E D I N STE E L B US H I N G
R e move t h e
a.
ex ist i n g
bushing
from the tab horn
an d re a m
t h e hole in the tab to
an
inside diameter of 0.3276!
0.3291 inch.
NOTE
Maintain the
bushing centerline
as
nearly perpendicular to
the trim tab tube centerline
Using a clean rag dampened with solvent (19, Consumable Materials Chart, Section
hole in the tab horn, the area around the hole and a P/N 96-610026-5 bushing.
b.
Scuff sand the contact surfaces of the
c.
bushing
and the tab horn, and clean the
2)
area
or
as
possible.
equivalent,
thoroughly
as
clean the
specified
in
step b.
d.
Wipe off
the parts with
clean rag before the solvent evaporates.
a
Apply a thin coat of adhesive (37,
bushing and the tab horn.
Consumable Materials Chart, Section
f.
and
e.
Join the tab horn and the
bushing
clamp together
2)
to the contact surfaces of both the
until the adhesive has cured
completely.
NOTE
When
Remove the
g.
a
clamping
existing
the horn and
rod end and locknut from the tab
P/N 96-610026-7 rod end,
h.
bushing together,
use care
not to squeeze out all of the adhesive.
pushrod assembly at the
tab horn end and
replace
it with
along with locknut.
Install the trim tab and install
a new
P/N AN173C6/M/ bolt in the tab horn end
on
the
pushrod.
NOTE
connecting the tab pushrod to the tab horn, the rod end must be free to move without binding
against the tab horn or the bushing in the tab horn. (Tu mi ng the nut on the bolt to contact the rod
end plus one castellation should accomplish this.)
When
i.
Lubricate all
pivotal points with grease (11, Consumable Materials Chart, Section 2).
ELECTRIC TRIM TAB SYSTEM
FIGURE 4-18
(O PTI O NA L)
ELECTRIC TAB ACTUA TOR REMOVAL
a.
Disconnect the actuator wire harness at the disconnect
b.
Place
a
wood
or
splices.
sheet metal shim between the cable drum and the cable
guard
to
prevent the cable from
un-
winding.
c.
Remove the fairlead from the bulkhead aft of the actuator.
d.
Discon nect the actu ator cable at the tu mbuckle fi rst, then at th e aft fitti ng.
e.
R emove the th ree bolts
4-46
securing
the actuator to the bracket,
remove
the actuator from the
airplane.
E16
BEECH BARON 55 AND 58 SHOP MAN UAL
ELECTRIC TAB A CTUA TOR INSTALLA TION
procedure is the
manu ally operated tab.
Installation
reverse
of the removal p roced u re. Tab
rigging
and cab I e te ns i o n
are
identical to the
NOTE
Adjust the variable
resistor mounted
within 1 8 to 20 seconds
applied
when 28 vdc is
on
adjacent to the
Model E55 ai rplan es
or
actuator until the cable travels from
with in 27 to 30 seconds
on
stop
to
stop
M ode 1 58 ai rp lanes
to the circuit.
TAB CA BL E REMO VAL
a.
Remove the fairleads and disconnect the cables at the turnbuckles.
b.
Connect
a
cable from the
lead line to the end of each forward cable
airplane
(identify
the line for
tab-up cable movement), and pull
the
structure.
and cable
guide
retaining pin
c.
Remove the cable
d.
Remove the cable from the cable drum.
from the cable drum.
TAB CABL E INS TALLA TION
Note the
the cable
same
will
position of
position. This
on
the cable drum in relation to the forward cable fittings. Install the new cable in the
on the d ru m i n both directions to allow full travel on the cable
ad eq u ate free cable
ensure
stops.
MA GNETIC CL UTCH REMO VAL
housing.
a.
Remove the lid from the clutch
b.
Loosen the setscrew in the clutch rotor and armature hubs.
c.
Rem ove the motor from the clutch
d.
Slide the cable drum and shaft
e.
Remove the clutch from the clutch
housing.
assembly
from the clutch
housing.
housing.
MA GNETIC CL UTCH INSTA LLA TION
procedure. No lubrication is required. Tighten the clutch armashaft. Slide the clutch rotor on the motor shaft to obtain 0.010
drum
in
cable
the
no
play
of the clutch before tightening the setscrew. Stake both setsurfaces
friction
the
between
of
inch
clearance
to 0.015
Installation
procedure is
ture setscrew with
the
reverse
of the removal
visible end
screws.
MA GNETIC CL UTCH TORQUE TEST
The
following
check should be
performed
any time the
magnetic
clutch is
replaced.
white
28 vdc power source, connect the red electrical lead of the magnetic clutch to ground and the
of
30
holds
with
clutch
inch-pounds torque
electrical lead to the power source. Using a torque wrench, check that the
a.
Using
applied
E16
a
at the actuator shaft.
4-47
BEECH BARON 55 AND 58 SHOP MAN UAL
b.
If the static torque of the clutch is less than 30
inch-pounds,
burn in the clutch
as
follows:
assemplate of sufficient thickness for rigidity and large enough to fit in a vise with the actuator
Bolt
holes.
actuator
the
mounting
bly attached. Anchor the plate in a vise and drill three holes in the plate to match
the actuator to the plate.
metal
1.
Find
2.
Slot the end of
the d rum is
a
a
tube that will fit
snugly
into the 0.437-inch-diameter hole in the end of the shaft
on
which
mou nted.
u ntil
3.
Insert the tu be i nto the shaft
4.
Attach the free end of the tube to
5.
Remove the
the
a
s lot
slow
engages the dru m
retaining pin.
speed (approximately
450
rpm)
half-inch drill motor.
and clutch clean with clean
dry air.
electrical lead of the clutch to
power source set at 14 to 16 vdc, connect the red
with
source
the
to
clips.
alligator
and the white electrical lead
power
ground
6.
Using
a
access
plate
from the clutch
housing
and blow the
housing
regulated
unclip the lead to the power source after 15 seconds. Let the clutch cool for approxuntil
imately one minute before reattaching the lead for another 1Ei-second interval. Repeat the foregoing sequence
clean
with
clean
and
clutch
the
blow
then
in
indicated
housing
step a,
the clutch will hold 30 inch-pounds of torque as
dry air.
7.
Start the drill motor and
CAUTION I
ICAVTION
Exceeding
the 15second burn-in
periods
may overheat and
damage the magnetic clutch.
MOTOR
LUTCH HOUSING
LUTCH ROTOR
mQL--~--e LUTCH
ARMATURE
.010 TO .015
O
Ih
SE TSC RE WS
ABLE DRUM SHAFT
COVER
CABLE DRUM
0------CABLE
RETAINING PIN
94~131´•8
Electric Trim Tab Actuator
Fig ure
4-48
4-1 8
E16
BEECH BARON 55 AND 58 SHOP MAN UAL
RUDDER AND TAB
RUDDER REMO VA L
navig ation lig ht
wi re and
the tail
a.
Detac h the tai I cone, disco n nect the tai I
b.
Remove the tail section
c.
Disconnect the rudder tab cables at the turnbuckles. Remove the cable retainer
d.
Re move the bolts
e.
Remove the rudder
access
attaching
hinge
doors
on
remove
the left hand side of the
fuselage.
pins and
the rudder torque tube to the bellcrank. Remove the
bolts and
remove
cone.
the fa i rlead.
bonding cable.
the rudder.
RUDDER INS TALLA TION
WARNING
IW~RNING)
Due to rudder imbalance the
airplane
must not be flown with the
rotating
beacon
light
removed from the rudder.
the holes in the rudder and stabilizer
hinges
and install the
attaching bolts.
a.
Align
b.
In stall the
c.
Connect the rudder tab cables at the turnbuckles. Install the cable retainer
d.
Check the travel of the tab and rudder tab indicator to
e.
Install the tail
attaching bolts through the
cone
Install the
bonding
cable.
rudder torque tube and bellcrank.
and connect the tail
light
wires.
see
pins
and fairlead.
that the tab and indicator agree.
Replace
the
access
doors.
RIGGING THE RUDDER CONTROL S YS TEM
FIGURES 4- 19, 4-20 AND 4-21
WARNING
IWARNINGI
replacing or installing control cables, bellcranks and other control system
components, on airplane serials TH-1389 and TH-1396 and after, observe the color coding
on all parts. Do not connect coded parts of one color to coded parts of a different color.
When
NOTE
Beech recommends the
use
of the
ru dd e r
trave I g ag e shown in the G EN E RAL I N FO R MAT ION
on the left side of the rudder at station 9.9.
section of this manual. Locate the travel gage
To
position the rudder pedals in the
at the
a.
E16
spacing
Place the rudder
shown in
pedals
Figure
in the aft
position for rigging, a tool can be fabricated from a steel
pins. The pins are parallel and located forward on the block
correct
block and two 3/8-inch-diameter steel
4-21.
position.
4-49
BEECH BARON 55 AN D 58 SHOP MAN UAL
b.
Install the rudder
pedal
pedal rig
pilot’s rudder pedals.
right rudder pedal.
tool in the holes in the
must be 0.38 to 0.45 inch aft of the
Refer to
Figure
4-19. The left rudder
NOTE
When the
rig tool
is installed
on
the
pilot’s
rudder
pedals,
the
copilot’s pedals
are
locked in the
same
position.
c.
Rig
the cables to the tension shown, then
remove
the
rig
tool. Refer to Fi g u re s 4-1 9
or
4-20. The rudder
bellcrank must be in neutral.
d.
Adjust
the rudder bellcrank travel stops to obtain 24" to 26" rudder travel left and
e.
C h ec k
ru dd e r
right.
t rave I.
WARNING
IWARNINGI
Check the rudder for correct direction of movement. When the left rudder pedal is
the rudder must move to the left. When the right rudder pedal is depressed, the
depressed,
rudder must
move
to the
right.
RUDDER TRIM TA B RIG GING
I
FIGURES 4-19 AND 4-20
NOTE
Beech
recommends the
use
of the rudder trim tab travel
gage shown
in the
GENE RAL
INFORMATION section of this manual.
a.
Set the rudder trim tab control
b.
Set t he
c.
Adjust the
d.
Disconnect the rudder tab
ru dd e r
that the indicator reads O"
(neutral).
i n neutral.
tab actuator
tral. Connect the
so
push-pull
e.
Center the chain
f.
Adjust the
g.
Ch eck tab travel.
on
so
that the tab actuator rod extends
push-pull
rod.
Adjust
the
length
a
little less than half its total travel.
of the
push-pull
rod to set the rudder trim tab in
neu-
rod to the actuator rod.
the actuator
sprocket
and
rig
the tab cable to the tension shown in
tab cable stops to obtain tab travel of 24" to 26" left and
right. Safety wire
Figures
4-19
or
4-20.
the turnbuckles and stops.
WARNING
IWAANINGI
Check the rudder trim tab for correct direction of movement. When the tab control is moved
to the left, the tab must move to the right. When the tab control is moved to the right, the tab
must
4-50
move
to the left.
El 6
Ra~heon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
W. S.
F. S
i
WING STATION
FUSELAGE STATION
L,
RIGHT RUDDER CABLE
I
TEMPERATURE CABLE TENSION GRAPH
UDDER TAB LDT
840
UDDER TAB RIGHT
C
RUDDW CABLE
8
1,
k
RUDDER BELLCRANK STOPS
I:i,
q~30
F.S. 272000
20
F.S. 262900
LEFTRUDDWCABLE
~S;1=/
A
RUOOER
CABLE
DFTAIL
F.S.
D
lo
:S 257606
233.50.S.
247.830
30
50
70
60
30
90
100
110
100
110
1EMPERATURE-5
TAB LEFT
RUDDER RIGHT
TAB CABLE STOPS
~FWDI
~--RUDDER
RUDDER LEFT-~
TAB RIGHT
i-o
.Y
40
DETAIL
NOTE: RIG AUTOPILOT CABLES AFTER CONTROL
SYSTEM CABLES ARERIGGED.
~M
z60
O
z
C
50
40
RUDDER CABLE
RUDDER CABLE
DETAILA
RUDDW TAB
RUDDER PEDAL
RIGGING HOLES
RUDDER
TAB RIGHT
~_
30
RUDDER TAB
LEFT~.,
RIGHT--~jr
LEFTRUDDERCABLE-’
RIGHT RUDDER CABLE-i
Ruuvr~-TAB LEFT
~MIM
20
B
A
2
DETAILB
~--F.S. 118.50
10
11200
30
40
50
60
80
70
90
TEMPERATURE- "F
5815523
Rigging
The Rudder Control
(TC-1 and After;
System
TE-1 and After; TH-I thru
TH-1388, TH-1390 thru TH-1395)
Figure
E16
4-19
4-51
BEECH BARON 55 AND 58 SHOP MAN UAL
THIS FAG E I NTE NTIO N AL LY LE FT B LA N K
4-52
E16
Raytheon Aircraft
BEECH BARON 55 AND 58 SHOP MANUAL
j/
RIGHT RUDDER CABLE
I
_
II
I
TEMPERATURE CABLE TENSION GRAPH
RUDDER CABLE
40
O
z
C
RUDDER TAB RIGHT -I
RUDDER CABLE
i
II r-I IB
z
BBLLCRANK STOPS
30
C
20
RUDDER CABLE
F.S. 272000.
10
~F"´• 262900
B
,r’
~C_
’F.S. 257.606
A~
30
40
50
.S. 247.830
RUDDER TAB LEFT
60
70
80
90
110
100
TEMPERATURE- "F
NOTE: RIG AUTOPILOT CABLES AFTER CONTROL
SYSTEM CABLES ARE RIGGED.
DETAIL
1
J
D
RUDDER TAB LEFT
IV
_b-;
B
I
z60
B
lT
LEFT RUDDER CABLE
\-F.S."3.50
I
RUDDER TAB
RIGHIg
RIGHT RUDDW CABLE
FWDI
50
LEFT RUDDER CABLE
RUDDER TAB RIGHT
FWDI
TAB
40
CABLESTOPS
30
oETAILA
I~J
TAB LEFT
d
DETAIL
C
20
RUDDER TAB RIGHT
RUDDER
CABLE
RUDDER TAB
LEFT-----4?5Y A
118.50
LEFT RUDDER
UDDW PEDAL
.S. 11200
RIGGING HOLES
10
RIGHT RUDDER CABLE
TAB RIGHT
UDDER
~RNDI
TAB LEFT
W. S.
F. S.
WING STATION
FUSELAGE STATION
DETAIL
B
~o
40
50
60
70
TEMPERATURE
80
90
llD
10Q
"F
5815~24
Rigging The Rudder Control System
(TH-1389, TH-1396 and After)
Figure 4-20
E16
4-53
BEECH BARON 55 AND 58 SHOP MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
4-54
El 6
BEECH BARON 55 AND 58 SHOP MANUAL
MEASURING THE R UDDER A ND RUDDER TRIM TAB TRA VEL IN INCHES
FIG URE 4 -22
When
as
a
travel gage is not available, rudder and rudder trim tab travel
can
be measured in inches rather than
degrees
follows:
Lightly clamp two strips
a.
the
ve rtical
of 1/4-inch
plywood
or
equ ivale nt to the rudder
trailing edge.
Exte nd them fo M/ard
along
stab i ii ze r.
b.
Pull the free ends of the
c.
Mark the
point
on
the tail
plywood firmly against
cone
that
the skin contour to fair the rudder to
corresponds to
the bottom
corner
of the rudder
neu tral
(0").
trailing edge. Refer to Figure
4-22).
d.
Figu re 4-22. All measu rements
straight line distance between the
the rudder and rudder tri m tab
are
shown in
in the TABLE OF RU DDER AND RUDDER TRIM TAB TRAVEL
are
the
The
given
position
points
used for measurement
of the surface at
ne utra I
(0")
on
and its
position
at maximum deflection.
Rig
Pin
C~L,
0. 38" to 0.45"
B-B
B
C;
9
B
´•ei0
~s,
L
A
A-A
Rig Pins: 3/8’’ dia. x2-1/8’’ Long
x l"x2"Long
Block:
55-1545
Rudder Pedal
Figure
E16
Rig Tool
4-21
4-55
BEECH BARON 55 AND 58 SHOP MANU AL
RUDDER TRIM TA 8 A C TUA TOR DISA SSEMBL Y
NG URE 4-23
all
wire.
safety
a.
Cut and
b.
Loosen the check nut
(1),
and
c.
Remove the
retaining
nut
(4) and
d.
Remove the
so roc ket
remove
retaining
asse m b ly (7).
e.
Remove the roll
f.
Remove the
screws
pins (10),
remove
screw
(3)
(2)
the
from the actuator
from the
sprocket housing (6),
remove
and the
bearings (8)
the actuator
from the
and
the actuator rod end
and
screw
(3).
housing (5).
pull
the back half of the ho using off of the
sprocket assembly.
bushings (9 and 12).
RUDDER TRIM TA B A CTUA TOR CLEA NING A ND INSPEC TION
Clean all parts in solvent
tion and excessive wear.
a.
and any other parts
b.
Replace bushings
c.
Lubricate the actuator
Section
2)
before
(15, Consumable
Materials Chart, Section
showing evidence of
2)
and
inspect
wear.
threads and beari n gs with lu bricati n g grease (1 1
screw
for cracks, corrosion, distor-
Consumable Materials Chart,
assembly.
RUDDER TRIM TAB A CTUA TOR ASSEMBL Y
FIG URE 4 -23
a.
Install the
new
holes, drill 0.094-
to clean all metal
Be
c.
Install the
d.
Install the shim
new
particles
bushing (12)
(11)
on
the
housing (5). Using the existing
holes through the new bushing.
the actuator
to 0.097-inch-diameter
b.
sure
bushing (9) in
and
filings
from the
holes in the actuator
housing
as
pilot
housing and bushing.
into the back half of the sp roc ket ho u s i n g
(6).
sprocket assembly.
55-1356
Rudder and Rudder Trim Tab Travel
Figure
4-56
4-22
E16
BE EC H BARON 55 AND 58 SHOP MAN UAL
sprocket assembly.
the
e.
Install the
bearings (8)
f.
Install the
sprocket assembly
g.
Align the
h.
Install the back half of the
sprocket housing using the retaining
i.
Install the actuator
(3)
j.
Safety
k.
Install the actuator rod end
holes in the
wire the
on
in the
housing.
sprocket assembly with the
screw
retaining
i n the
housing
holes in the
housing and bushing,
and i nstall the retai ni ng nut
tighten
the actuator
screw
and
between the actuator
screw
and the
on
Safety
wire the
retaining
pins (1~).
screws.
(4).
pins (10) together.
nut and the roll
(2)
screws.
then install the roll
the check nut
(1). Safety
wire the check nut to
the actuator rod end.
i.
Check that the end
play
housing
does not exceed 0.011 inch.
TABLEOF RUDDERAN D RUDDER TRIM TAB TR AV E L I N I N C H ES
Maximum
Direction
Surface
Minimum
Measuring
Point
Rudder
R and L
9.60
or
(26*)
8.88
or
(24*)
Bottom
corner
of
trailing edge
Rudder Trim Tab
R and L
4.50
or
(26*)
4.16
or
(24*)
Bottom
corner
of
trailing edge
C~z12
i. ChBCk NUt
2. Actuator Rod End
3. Actuator Screw
4. Retaining Nut
6
5.
Housing
6.
Sprocket Assembly Housing
Sprocket Assembly
Bearing
Bushing
7.
8.
9.
5
10. Roll Pins
11. Shim
12.
Bushing
10
58´•163´•5
Rudder Trim Tab Actuator
Figure
E16
4-23
4-57
BEECH BARON 55 AND 58 SHOP MANUAL
CHECKING RUDDER TRIM TAB FREE PLA Y
FIG URE 4-24
syste m. I n co n si ste nc ie s
A ch ec k fixtu re
loading
a.
damage, security of hinge attach points, and for tightness of the
cc rrected before checking the free play of the tab.
the rudder trim tab for
Visually inspect
(P/N
to the tab
m u st
be
0) or equivalent, a dial indicator, and a pus h-pu II scale for applying
the inspection for tab free play. Refe r to Fi g u re 4-24.
for
uired
making
req
45-1 35030-9/81
are
Secu re ly lock the
co ntro I s u rf aces
to
prevent
point
Use tape to hold the dial indicator check fixture so that the
hinge line and on the bottom edge of the rudder tab.
Apply
a
of the dial indicator is 8.10 inches aft of the tab
piece of masking tape (for paint protection) 9.5 inches aft of the tab hinge line
actuator. This is the point of pressure against the tab by the push-pull scale.
small
terline of the tab
another
piece
Apply
e.
Set the dial indicator at
f.
With the
g.
Release half of the load to obtain
h.
On the
i.
Release half of the load to obtain
j.
Enter the recorded
push-pull
B
on
on
the
masking tape, apply
a
on a
2 and record
a
pound
location
on
during
the
pound
3.0
Subtract A from 2B and record
3.
Multiply
4.
Subtract C from 2D and record
as
pound
a
3.0
pound
right.
as
Record the dial
reading
as
as
reading
as
A.
B.
load to the left. Record the dial
proceed
cen-
checking procedure.
reading
load. Record the dial
along the
the other side of the tab.
load to the
load. Record the dial
and
reading
as
C.
D.
follows:
28.
2.
2 and record
1.5
apply
a
copy of Chart 4-3 and
Multiply
by
1.5
the left surface,
readings
corresponding
Do not reset the dial indicator
1.
D
by
zero.
scale
masking tape
in the
masking tape
of
d.
accurate
movement of the rudder. Set the rudder trim tab in neutral.
b.
c.
actu ating
as
as
X.
2D.
as
Y.
NOTE
X and Y
5.
k.
Add X and Y and record
If the free
play
is
over
to determine the cause.
4-58
as
worn
be
negative
numbers.
E.
the maximum
All
can
parts
specified in Chart 4-3, inspect
replaced.
all
components of the tab
actuator
system
must be
816
BEECH BARON 55 AND 58 SHOP MAN UAL
C HA RT 4-3
RUDDER TA BFREE PLAY LIMITS
1.5-POUND
3-POUND
READING
READING
B
2B
-A
=X
2D
-C
=Y
X
+Y
=E
E
0.090 inch maximum
VERTICAL STABILIZER
VERTICAL S TABIL IZER REMO VAL
Remove the tail section
access
doors
on
the left hand side of the
I.
Remove the rudder. See RU DDER REMOVAL.
m.
Remove the
n.
R e m ove the attac h i ng bolts at the forward and
screws
securing the fairings
fuselage.
to the vertical stabilizer.
rear
spars and
remove
the center
hinge
bracket from the lower
center spar and remove the stabilizer.
VERTICAL S TABILIZER INS TA LLA TION
a.
Position the vertical stabilizer and install the bolts
1.
On
airplanes TO-1 through TC-2456,
as
follows:
through TE-1201 and TH-1 through TH-1483, torque the bolts at
the
190 inch-pounds. Install the elevator center hinge bracket on
TE-1
the forward soar and upper rear spar to 160 to
bottom of the rear spar and torque the bolts to 50 to 70
inch-pounds.
and
On TC-2457 and after, TE-1202 and after and TH-1484 and after, torque the bolts at the forward spar
bracket on the bottom of the rear spar
upper rear spar to 330 to 360 inch-pounds. Install the elevator center hinge
and torque the bolts to 85 to 100 inch-pounds.
2.
fairings.
b.
Install the vertical stabilizer
c.
Install the rudder. See RUDDER INSTALLATION in this section.
d.
I nstall the
E16
access
doo rs.
4-59
BEECH BARON 55 AND 58 SHOP MANUAL
9
12
to
678
13
5
11
j
.8 IN
-t
I
\II I
.5 IN
.25 IN
1d
1.25
TYP,
L~
5/8-11
rAP
I
2.9 IN
t
4
AA--L
t
TAB
14
/1
\1
1.30 IN
ITEM
QUANT.
DESCRIPTION
~n
-t
NO.
.68 IN
1 x 6 aluminum or
1
2
3/4
2
2
1
3
1
1/2
4
1
C81Q Indicator"
5
1
3/4
x
x
1 3/8
x
x
x
7 1/2
2 112
equiv.
equiv.
equiv.
1 3/4 aluminum or
x
x
10 alumirmm or
14 aluminum
stl.
t
1/4 Dia. x2 corrosion
7
1
1/4 Die. xlcorrosion res. stl.
8
1
1/4-28 nut
9
1
10
1
3/8 x5x10 rubber
3/8 x2x10 rubber
11
1
1/4 x2x10 corrosion
12
2
13
2
14
2
"P/N of Federal Products
2/1.lTorque
ts
x
13
x
res.
3 VLIER
KN813 Keensert or tap 112
118 x 1 x 3/4 rubber
Corp., Providence,
R. I.
1.6 1N
equiv.
or
6
res.
-L---tt
screw
.31 IN
_I
L~
sE CTION A A
13
THIS GROOVE TO BE A SNUG FIT
TO THE SCREW BRACKET ON
’IH E DIAL IN DICATOR
100´•135-8
Fabricating Clamp for Tab Deflection
Figure 4-24
4-60
E16
BEECH BARON 55 AN D 58 SHOP MAN UAL
H ORIZO NTA L STABILIZER
HORIZONTAL S TABIL IZER REMO VAL
a.
Detach the tai I cone, d isco n nect the tail navi gation
b.
Remove the tail section
c.
Remove the elevator. See ELEVATOR REMOVAL.
d.
Loosen the elevator trim tab cables at the turnbuckles
doors
access
on
lig ht
an d remove
wi re
the left hand side of the
at the connection in the aft tail section. Remove the
pulleys
just
cone.
fuselage.
aft of the
from the
the tail
rear
pulley
cabin bulkhead and disconnect them
brackets aft of the disconnect to free the
cables.
e.
Remove the stabilizer
f.
R emove the stab i I i ze rs.
attaching
bolts at the forward and
rear
spars.
HORIZONTAL STABILIZER INS TA LLA TION
Position the stabilizers
the
fuselage and install the attaching bolts in the forward and rear spars. On TC se(except TC-350), torque the bolts to 85-100 inch pounds. On TE, TH and TC serials (TC-350,
TC-2457 and After), torque the forward spar bolts to 200-225 inch-pounds dry and torque the rear spar bolts to
85-100 i nch-pou nds d ry.
a.
rials
prior to
on
iC-2457
b.
Route the tab cables back
c.
Install the elevate r. See E LEVATO R INSTA LLAT I O N.
d.
Con nect the elevate r tab actuate r rods.
e.
Rig
f.
I nstall the
through
the
fuselage
and connect the cables at the turnbuckles.
the trim tabs.
access
doo rs.
I
If
new
stabilizers
balance must be
are
installed
on an
CAUTION
CAUTIQN
airplane prior
I
to serials TC- 1144 and
TE-618, weight and
computed.
BA LAN C IN G CO NTRO L S U R FAC E S
I
AILERON
BALANCING TH E AILERON
FIGURE 4-25
When the aileron control
toward the
su rface
is
being repainted, suspend
it
by
the
trailing edge
so
t h at
exe es s
wil I drai n
leading edge.
After any modifications, repairs or repainting, the finished surf ace must be check balanced to
moment about the hinge line is within the prescribed limits.
E16
pal nt
ensure
that its static
4-61
BEECH BARON 55 AND 58 SHOP MAN UAL
painted aileron assembly must be nose-heavy by 0.2 to 1.5 inch-pounds. The right-hand painted aileron assembly must be nose-heavy by 0.2 to 1.5 inch-pounds. The static moment of the aile ron is determined by
mu itiplying the unbalanced weight of the aileron assembly times the perpendicular distance from the h i nge ce nte rline to the center of gravity when the chord line is horizontally level. The weight is measured in pounds and the distance in inches. The static moment of a100 percent balanced control surf ace is 0.0 inch-pounds. A tail-heavy
s u rf ac e ex h i bits stati c u n d e rba I ance. A nose-heavy surface exhibits static overbalance.
The left-hand
CHECKING BALANCE
completely assembled in flying condition.
push rod, static wic ks and hinge bolts
touch-up,
completed.
stripes
must be attached. The chord line must be horizontally level and the hinge line must be prope rly su pported when the
static moment is measured. Although many different methods of check balancing exist, they can be categorized under the following two headings:
T h e ai le ro n balance must be checked in
Al I
pal nti ng, in cl ud i ng
Counterbalancing
a.
a
draft-free
The
of
application
a
b.
with the aileron
The tab, tab
known force
counter the unbalance moment of the aileron
a
area
must be
and
or
weight
a
measured distance from the
hinge line
to
assembly.
A measurement of the force
Actual Force Measurement
known distance from the centerline of the
at
aileron surface
applied by the
on a
single support
at
hinge.
NOTE
Counterbalancing is
the
simplest
method of check
balancing.
COUNTERBALANCING METHOD
CHECK BALANCE BY COUNTERBALANCING
The
a.
equipment required
A stand with
to
perform
by counterbalancing is
the check balance
knife-edge supports
as
illustrated in
Figure
4-25. The knife
as
follows:
edges
must be in the same horizontal
plane.
I
lightweight
b.
A paper cup
c.
App roxi m ate ly
d.
A certified beam balance
e.
A
or
similar
container.
1 po u nd of lead shot.
straightedge, ruler,
and
weighing
spirit
device calibrated in units of 0.01
pound
or
less.
level.
BALANCING PROCEDURE COUNTERBALANCING METHOD
a.
the
Locate the chord line
by placing
a
straightedge
and the other end is centered
trailing edge
grease pencil,
as a
then
remove
the
Secure the trim tab
c.
Fit the correct size bolts in the
(LH only)
leading edge.
assembly so
Mark the chord line with
a
that
one
end is
on
suitable marker, such
straightedge.
in its neutral
b.
on
at the inboard end of the aileron
the
position
hinge brackets and
hinge line.
with
a
small
piece
mount the aileron
of
on
masking tape.
the
knife-edge supports.
Ascertain that
the aileron is free to rotate about the
weig ht should be added or removed, suspend a paper cup from a point near the center of the
aileron trailing edge. Use a short length of small diameter string secured to the surface with a small piece of masking
tape as illustrated in Figure 4-25. The cup must be free to hang vertically.
d.
To determine if
4-62
E16
B E EC H BARON 55 AND 58 SHOP MAN UAL
e.
holding
f.
quantities of lead shot to the cup until the aileron
spirit level aligned with the marked chord line.
Add small
the
perpendicular to
The distance D must be
the
hinge
balances with the chord line level. Check this
line. Measure D fro m the
hinge
line to the
by
suspension point
of the cup.
Remove the cup, contents, and
g.
then
string,
weigh
them.
NOTE
Since any weighing error is magnified by the distance D,
done carefully on scales that are certified for accuracy.
h.
Calculate the static balance
as
The
weight
2.
The
over- or
3.
M=WXD
4.
The
underbalance
following
is
a
is most
important
and
mu st
be
follows:
of the cup and contents is
1.
weighing
i s d es i g nated
mo me nt
typical example
designated by
of
a
by
W.
M.
balancing calculation: Assume the aileron is overbalanced (noseedge. Assume that the aileron balances with the chord
and the paper cup was suspended from the trailing
line level at W
0.150 pound and D=10.0 inches, then...
heavy)
M
0.150 X 10.0
M
1.50
inch-pounds.
In this instance, M is within the
i.
product
required
of W X D.
static balance range and is therefore
acceptable.
painted aileron assembly must be nose-heavy by 0.2 to 1.5 inch-pounds. If the static balance does
weight may be added or removed to obtain static overbalance, as illustrated in Figure 4-25.
The
ply, pig
The
not
com-
lead
ELEVATOR
BALANCING TH E ELEVATOR
FIGU RE 4-26
being repainted, suspend it by the trailing edge so that excess paint will drain
After
modifications,
repairs, or repainting, the finished surf ace must be check balanced
leading edge.
any
to ensure that its static moment about the hinge line is within the manufacturers prescribed limits. The complete elevator assembly, painted or unpainted, including the control arm and the tab control rod mu st not be tail-heavy over
When the elevator control surface is
toward the
the maximum moment noted
as
follows:
NOTE
A
a.
22.6
tail-heavy su rf ace
exhibits static underbalance. A
inch-pounds
on
TO-1
through TC-546 equipped
inch-pounds
on
TC-1
through TC-546 equipped
nose-heavy surface exhibits
with
original
static overbalance.
skin orauthorized spare
replacement beaded
skin.
b.
18.0
with authorized spare
replacement smooth skin
eleva-
tor(s).
E16
4-63
BEECH BARON 55 AND 58 SHOP MAN UAL
~3´•0lf,
Jlo MUST )E HOR IZO NTALCI LEVEL
ACTUAL FORCE M5ASURMENT
METHOD
A
B
MASKING TAPE
(TO SECURE TAB
IN NE UTRAL)
.I
KNIFC~EDGE
STEEL TUBE WITH PIO
LEAD
MASKING TAPE
(PLACE NEAR AILERON HINGE LINE)
D
I-
~10 MUST IE H O it 1Z O NTA LLY L EV EL
VIEW
DETAIL
A-A
ss151n*
Bal a n ci ng th a Ai le ron
Figure
4-64
4-25
E16
BEECH BARON 55 AND 58 SHOP MANUAL
17.5 i nch-pou nds
c.
on
through
TC-502
d.
18.0 inch-pounds
placement.
on
TC-547 and after
inch-pounds on TE-1 through
replaceme nt 1 2.4 in. Ibs.
e.
12.4
f.
14.0
inch-pounds
on
equipped with original beaded skins
airplanes with utility baggage door.
TC-546
authorized spare rep raceme nt bead ed skin for
equipped
with smooth skin
TE-875 and TH-1
through
TE-876 and after and TH-258 and after
original
TH-257
and
eq ujpment
equipped
with
equipped with original
utility baggage
or
authorized spa re
original
or
door
or
re-
authorized spare
or
authorized spare
replace-
ment.
CHECKING BALANCE
a draft-free a rea with the elevator completely assembled in flying conditouch-up, must be completed. The tab, tab pushrod, static wicks, and hinge
bolts must be attached. The chord line must be horizontally level and the hinge line must be properly supported when
the static moment is measured. Although many different methods of check balancing exist, they can be categorized
under the following two headings:
The elevator balance must be checked in
tion. AIl
incl udi ng
Counterbalancing
a.
cou nter
b.
a
painti ng,
stripes
The
and
application
of
a
known force
the unbalance moment of the elevator
Actual Force Measurement
or
weight
measured distance from the
a
hinge line
to
assembly.
A measurement of the force
known distance from the centerline of the
at
applied by
the elevator surface
single support
on a
at
hinge.
FORCE MEASUREMENT METHOD
I
CHECK BALANCE B Y FORCE MEA SUREMENT
The
a.
equipment required
A stand with
to
perform
the check balance
knife-edge supports
as
illustrated in
by force
measurement is
4-26. The
Figure
as
knife-edges
follows:
should be in the
same
horizontal
plane.
b.
A certified beam balance calibrated in units of 0.01
form and its
capacity should equal
c.
A support
d.
A
tare
plus
a
spindle similar to the illustrations
straightedge,
rule and
spirit
pound
or
less. The balance should have
a
flat
weighing plat-
minimum of 2.0 pou nds.
and
leveling blocks,
as
required. (Blocks
spindle
tare).
level.
BALANCING PROCEDURE FORCE MEASUREMENT METHOD
a.
Locate the chord line
by placing
a
straightedge
at the inboard end of the elevator so that
the center of the torque tu be and the other end is centered
b.
Mark the chord line
c.
F it
cc rrect s ize d
by grease pencil
Support
E16
means on
hinge
the
one
end is
aligned
with
trailing edge.
the rib. Remove the
hinge brackets
straightedge.
and mount the elevator
on
the
knife-edges.
line.
trailing edge behind the center hinge point spindle resting on
spindle must be vertical throug hout the balanci ng p rocedu re.
the
illustrated. The
other
bolts in the outboard and center
Ensure that it is free to rotate about the
d.
or
on
a
leveled beam bala nce
platform
as
4-65
BEECH BARON 55 AN D 58 SHOP MAN UAL
Hold
e.
a
spirit
level
chord line and level it
against the marked
spindle.
by extending
or
contracting
the
spindle,
or
by using
blocksandshims underthe
distance from the
hinge centerline
to the
f.
Measure the
g.
Ensure that the
h.
Calculate the static underbalance moment M from the formula:
perpendicular
level and rule
spirit
are
point supported by
removed from the surface and read the reaction
spindle.
the
on
the beam balance.
(R-T) inch-pounds where,
M
D
D
Perpendicular
R
Reaction
T
Tare, i.e., spindle plus leveling blocks
distance from the
(pounds)
hinge
centerline to the
spindle point (inches).
read from the beam balance.
shims
or
on
the scale
platform (pounds).
EXAM P LE
D is 13.5 inches, R is 1.89 ib. and T =1.00 ib.
M=13.5(1.89-1.00); M=12.0inch-pounds.
satisfactory.
M is within the range which is
If M is not within the
prescribed
RE COU NTERBALANCING
range, refer to step i. under BALANCING P ROCEDU
METHOD.
I
COUNTERBALANCING METHOD
CHECK BALANCE BY COUNTERBALANCING
I
The
a.
equipment required
A stand with
to
perform
the check balance
knife-edge supports
as
illustrated in
by
cou
Figure
nterbalancing
4-26. The
is
a
follows:
knife-edges
must be in the same horizontal
plane.
A paper cup
c.
Approximately
d.
A certified beam balance
e.
A
or
similar
lightweight
b.
2
of lead shot.
pounds
straightedge, ruler,
container.
and
weighing
device calibrated in
u nits
of 0.01 pou nd
or
less.
spirit level.
BALANCING PROCEDURE COUNTERBALANCING METHOD
a.
on
Locate the chord line
the
such
hinge
as a
by placing
straightedge
centerline and the other end is centered
grease
pencil,
then
remove
b.
Secure the trim tab in its neutral
c.
Fit the correct size bolts in the
the elevator is free to rotate
4-66
a
the
at the inboard end of the elevator
on
the
trailing edge.
assembly
Mark the chord line with
so
a
that
one
end is
suitable marker,
straightedge.
position
with
a
small
hinge devises and
about the hinge line.
piece
of
masking tape.
mount the elevator
on
the
knife-edge supports. Ascertain that
E16
BEECH BARON 55 AND 58 SHOP MANUAL
weight should be added or removed, use a short length of small-diameter string secured to the
a
piece of masking tape and a cup hanging vertically as illustrated in Figure 4-26. Slightly loosen
the forward top screw on the tip of the elevator leading edge. Suspend a paper cup on the inboard side of the tip
and wrap the string around the screw. Secure the string to the surface with a small piece of masking tape aft of the
top forward screw and near the hinge center line as shown in Figure 4-26. The cup must be free to hang vertically.
d.
To determine if
surface with
small
CAUTION 1
JCAVTION
Be certain the forward top
screw on
the
tip of the
elevator leading
edge
is secured after the elevator
has been balanced.
e.
holding
f.
quantities of lead shot to the cup until the elevator
spirit level aligned with the marked chord line.
Add small
the
The distance D must be
perpendicular to
the
hinge
balances with the chord line level. Check this
line. Measure D fro m the
hinge line
to the
by
suspension point
of the cup.
g.
Remove the cup, contents, and
string,
then
weigh
them.
NOTE
weighing error is magnified by
carefully on scales that are certified
Since any
done
h.
Calculate the static ba la nce
1.
The
weight of
2.
The
over- or
3.
M=WxD
as
weighing
is most
important
and must be
fo I I ows:
the cup and contents is
underbalance
the distance D,
for accuracy.
mome nt
designated by
is desi g nated
by
W.
M.
The following is a typical example of a balancing calculation: Ass ume the elevator is u nde rbalan ce (tai Ithe paper cup was suspended from the horn. If the elevator balances with the chord line level at
and
heavy)
W
12.6 inches, then
0.95 pound and D
4.
M
0.95 X 12.6
M =12.0
inch-pounds
In this instance, M is within the
required
static balance range and is therefore
acceptable.
complete elevator assembly, painted or unpainted including the control arm and the tab control rod, must
not be tail-heavy over a maximum moment (see ELEVATOR BALANCING for applicable airplane serials and maximum moment). If the static balance does not comply, remove the elevator horn cover and add or remove solder to
bring the elevator balance within required limits.
i.
The
NOTE
Coat the
weight
with
dissimilar metals.
E16
a
corrosion
Replace
preventative material such
the elevator horn
cover
as
zinc chromate
primer
to insulate the
and recheck the balance.
4-67
BEECH BARON 55 AND 58 SHOP MAN UAL
COUNTERBALANCING
MASKING TAPE
(PLACE
HINGE
CO NTAIN ER
VIEW
NEAR ELEVATOR
LINE)
A-A
70P FORWARD 5CREW
JIG MUST BE HaalZONIALLV
LEV EL FOR UNDERBA LANCE CHECK
A
B
MASKING TAPE
DETAIL
B
~CONTAIN ER
MASKING TARE
(TO SECURE~ABIN NE UTR AL)
I
ELEVATOR
HINGE
CLEVIS
KNIFE EDGE
JIO MU 5T BE HOR1ZONfALLr
’C;SLLL~
LEVEL
Balancing
the Elevator
Figure
4-68
56-1528
4-26
E16
BE ECH BARON 55 AND 58 SHOP MANUAL
RUDDER
BALANCING THE RUDDER
FIGURE 4-27
WARNING
IWAANING(
Due to rudder imbalance the
airplane
must not be flown with the
rotating
beacon
light
removed from the rudder.
When the rudder surface is
being repainted, suspend
it
by the trailing edge
so
that
excess
paint will
drain toward the
leading edge.
After any modifications, repairs or repainting, the finished surface must be check balanced to ensure
that its static mo me nt about the hinge line is within the manufacturer’s p resc ri bed I i m its. The complete rudder as-
sembly, painted
unpainted including the control arm and with or without the bellcrank attached, on serials TO-1
tail-heavy over a maximum of 1 5.0 inch-pou nds. On serials TE- 1 and after and TH-1 and af te r,
the complete painted rudder assembly, with or witho ut the bellcrank attached, shall not be tail-heavy over a maximum of 4.5 inch-pounds. The static moment of the rudder is determined by multiplying the unbalanced weight of the
rudder assembly times the perpendicular distance from the hinge center line to the center of gravity when the chord
line is horizontally level. The weig ht is measured in pounds and the distance in inches. The static moment of a 1 00
percent balanced ru dd er assemb ly is 0.0 inch-pounds. Tail heaviness indicates static underbalance while nose
or
and after, shall not be
heaviness indicates static overbalance.
CHECKING BA LA N C E
The rudder balance must be checked in a draft free
All painting, including stripes and touch-up, must be
completely assembled in flying condition.
completed.
push rod, static wicks, and hinge bolts
must be attached. The chord line must be horizontally level and the hinge line must be properly supported when the
static moment is measured. Although many different methods of check balancing exist, they can be categorized under the following two headings:
Counterbalancing
a.
The
application
of
a
b.
a
Act u al Fo rce Measurement
The tab, tab
known force
counter the unbalance moment of the rudder
with the rudder
area
or
weight
a
measured distance from the
hinge
line to
assembly.
A measurement of the force
known distance from the center line of the
at
applied by the
rudder surface
on a
single support
at
hinge.
FORCE, M EASU R E M ENT METH OD
I
CHECK BAL4NCE B Y FORCE MEA SUREMENT
The
a.
equipment required
A stand with knife
to
perform
the check balance
edge supports
as
illustrated in
by force
Figure
measurement is
4-27. The knife
as
edges
follows:
should be in the
same
horizontal
plane.
b.
A certified beam balance calibrated in units of 0.01 ibs.
and its
capacity
should
equal
tare
plus
or
less. The balance should have
c.
A
support spindle similar to the illustration and leveling blocks,
d.
A
straightedge,
El 6
rule and
spirit
a
flat
weighing platform
2.0 ibs. minimum.
as
required. (Blocks
spindle
tare).
level.
4-69
BE EC H BARON 55 AND 58 SHOP MAN UAL
BALANCING PROCEDURE FORCE MEA SUREMENT METHOD
by placing
Locate the chord line
a.
a
straightedge
at the lower end of the rudder
center of the torque tube and the other end is cente red
Mark the chord line
b.
by grease pencil
or
other
Fit correct size bolts in the upper and center
hinge line.
c.
on
the trail ing
means on
and
aligned
with the
edges.
Ensu re
leveled beam balance
platform
that
one
end is
edge.
the rib. Remove the
hinge brackets
so
mou nt
straightedge.
the rudder
on
the knife
that it is free to rotate about the
d.
as
Support the trailing edge behind the center hinge point with a spindle resting on
illustrated. The spindle must be ve rtical throughout the balancing procedure.
e.
Hold
a
spirit
chord line and level it
against the marked
under the spindle.
level
blocks and shims
perpendicular
distance from the
by extending
hinge centerline
to the
f.
Measure the
g.
Ensure that the
h.
Calculate the static underbalance moment M from the formula:
and rule
spirit level
are
or
a
contracting
the
point supported by
removed from the surface and read the reaction
spindle,
the
on
or
by using
spindle.
the beam balance.
(R-T) inch-pounds where,
M
D
D
Perpendicular
R
Reaction
T
Tare; i.e. spindle plus leveling blocks
distance from the
(pounds)
hinge
center line to the
spindle point (inches).
read from the beam balance.
or
shims
on
the scale
platform (pounds).
EXAM PLE
1.87 ib. and T is 1.00 ib.
D is 13.8 inches, R
M=13.8(1.87-1.00);
satisfactory.
M is within the range which is
If M is not within the
prescribed
inch-pounds
M=12.0
NTERBALANCING
range, refer to step i. under BALANCING P ROCEDU RE COU
METHOD.
I
COUNTERBALANCING METHOD
CHECK BALANCE BY COUNTERBALANCING
I
The
a.
equipment required
A stand with
to
perform
the check balance
knife-edge supports
as
illustrated in
by counterbalancing
Figure
4-27. The
is
as
follows:
knife-edges
must be in the same horizontal
plane.
b.
A paper cup
c.
Approximately
d.
A certified beam balance
e.
A
4-70
or
similar
2
light weight
pounds of
straightedge, ruler,
and
container.
lead shot.
weighing device
spirit
calibrated in units of 0.01
pound
orless.
level.
El 6
B E E C H BARON 55 AND 58 SHOP MAN UAL
BALANCING PROCEDURE COUNTERBALANCING METHOD
Locate the chord line
a.
by placing
a
straightedge
at the lower closure rib of the rudder so that
with the center of the torque tube while the othe r end is cente red on the
suitable marker, such as a grease pencil, then remove the straightedge.
trailing edge.
b.
Secure the trim tab
of
c.
Fit the correct sized bolts in the
position
in its neutral
position with
hinge brackets
hinge line.
a
small
piece
and mount the rudder
on
one
end is
aligned
Mark the chord line with
a
masking tape.
the
knife-edge supports.
Ascertain that
the rudder is free to rotate about the
weight should be added or removed, suspend a paper cup from a point near the center of the
trailing edge if the balance is nose down or near the center of the leading edge if the balance is tail down.
Use a short length of small-diameter string secured to the surface with a small piece of masking tape as illustrated
in Figure 4-27. The cup must be free to hang vertically.
d.
To determine if
rudder
e.
Add small
holding
f.
a
quantities of lead shot to the cup until the
spirit level aligned with the m arked cho rd I i n e.
The distance D must be
perpendicular to
the
hinge
rudder balances with the chord line level. Check this
line. Measure D from the
hinge
line to the
by
suspension point
of the cup.
g.
Remove the cup, contents, and
string,
then
weigh
them.
NOTE
h.
Since any
the distance D,
done
for accuracy.
weighing error is mag nified by
carefully on scales that are certified
Calculate the static balance
1.
The
2.
The over’-
3.
M=WxD
4.
The
(tail heavy)
at W
In this
weight
designated by
W.
underbalance moment is
designated by
M.
is
a
pound and D
0.35
M
3.5
instance,
x
important
and must be
balancing calculation: Assume the rudder was slightly underbalance
paper cup was suspended from the leading edge. If the rudder balances with the chord line level
following
M
is most
follows:
of the cup and contents is
or
and the
0.35
as
weighing
typical example
of
a
10.0 inches then...
10.0
inch-pounds
M is within the
required
static balance range and is therefore
acceptable.
i.
The complete rudder assembly, painted or unpainted, including the control arm and with or without the bellcrank
attached, must not be tail-heavy over a maxi mu m mo me nt (see R U DDER BALANCING for applicable airplane se-
rials and maximum
move
solder to
moments). If the static balance does not comply,
bring the rudder balance within required limits.
remove
the rudder-horn
weight
and add
or re-
NOTE
Coat the
weight with a corrosion preventative material such as zinc
Replace the rudder horn weight and recheck the
dissimilar metals.
E16
chromate
primer to
insulate the
rudder balance.
4-71
B E EC H BARON 55 AND 58 SHOP MAN UAL
AC 32.976
C
DETAIL C
~´•-1
A
MASKING TAPE
CONTAINER
RUDDER
(NEAR
HINGE
MA SKINO TA Pf
(NEAR RUDDER-/
HINGE LIN f)
LINE)
CONTAINER
MASKING TA PE
TO SECURE TAB
IN NEUTRAL
c,,
KNIFE EDGE
ACTUAL FO RCE MEASUR EMENT
CONTAINER
vrEwA-A
JIO M U ST BE HORIZO NTALLI L EVEL
JIO MUST BE HORIZONTALLY LEVEL
STATIC UNDERBALANCE
(TAIL HEAVY)
ICONTAINER
VIEWB-B
JIG MUST BE HORIZONTALLY LEVEL
STATIC OV ER B ALAN C E
Balancing
H EAVY)
6b15)S
the Rudder
Figure
4-72
(N O S E
4-27
E16
SEECH BARON 55 AND 58 SHOP MANUAL
FLAPS
FUA P REMO VAL
FIG URE 4-28
a.
Rem ove the bolt from the
b.
Remove the
c.
Remove the bolts from the rollers in the
bonding
flap actuating
cable from the
arm.
flap.
flap
track and
remove
the
flap.
FLA P INS TALLA TION
FIG URE 4-28
a.
Hold the
flap
in
position
and install the rollers and bolts in the
flap
track.
NOTE
In stall the
flanges
b.
flap
track rollers
of the rollers in
Connect the
bonding
one
(four
track
rollers per flap and two rollers per track) in the flap track with the
facing the flanges of the rollers in the other track.
cable and install the bolt in the
flap actuating
arm.
FLAP TRA CK WEA R L IM1 TS
The allowable track wear on the bearing surfaces is 0.032 inch, resulting in a maximum dimension of 0.785 inch for
the slot in the flap track. The allowable wear into the track side surface is 0.050 inch.
Track
wear within the preceding limitations can be dressed smooth with fine emery cloth to prevent ro lier binding.
Lubricate the tracks with Molykote Z mixed with naphtha (12 and 18, Consumable Materials Chart, Section 2),
brushed on the flap tracks.
FLAP ACTUATOR
FLAP DRIVE SHAFT
AND HOUSING
FLAP ACTUATOR
MOTOR
LIMIT
SWITCHES
FLAP DRIVE SHAFT
AND HOUSING
FLAP
ACTUATOR
58-161-17
Flap System
Figure
El 6
4-28
4-73
BEECH BARON 55 AND 58 SHOP MAN UAL
FLAP LIMIT SWITCH ADJUSTMENT
FIG URE 4 -29
NOTE
Battery voltage is not su fficie nt to cycle the flaps correctly during rigging. Use an auxiliary power
supply capable of maintaining 28.00 to 28.50 vdc. If an external power receptacle is not provided
on the airplane, jumper cables can be used betwee n the batte ry an d the powe r s u pp ly. Be su re of
the polarity before connecting the power supply.
flap limit switches are mou nted on a bracket and
wing. They are accessible by lowering the flaps.
The
left
installed
on
the outboard side of the inboard
flap
track in the
CAUTION I
I cAuTlon
Operation
of the
flap
motor without
adequate cooling
cycle.
can
damage
the motor. Allow
a
brief cooling
time after each extension and retraction
The limit switches control the travel of the
The
flap
travel is
with the left
adjusted by moving
the
flaps by breaking the circuit to the flap motor at the extreme limits of travel.
limit switches. Rig the left wing flap first, then synchronize the right flap
flap.
APPROACH POSITION SWITCHES
(THREE POSITION FLAPS)
DOWNLIMIT
rp
SWITCHES
UPtlMIT SWITCH ES
58-161-16
Flap Limit
Switches
Figure
4-74
4-29
E16
BEECH BARON 55 AND 58 SHOP MANUAL
TWO-POSI TION FLA PS
(TC- I
THRU
TC-2002)
NOTE
Beech recommends the
use
of the
Two limit switches control the
loosen the
screws on
gage shown in the GENERAL INFORMATION section
the flap just aft of the flap actuator.
flap travel
of this manual. Position the travel gage
on
uplimit position and the downlimit position. To adjust the flap to neutral (UP position),
assembly so that it can pivot on the forward elongated hole. Adju st the switch to
the switch
stop the flaps in neutral.
NOTE
Rig
the
flaps under
simulated
a
flight
load to minimize overtravel
(coasting)
of the motor after the
ii m it switc h h as be e n actu ated.
Move the flap control switch to the down position and
downlimit switch to obtain 28" to 30" of down travel.
THREE-POSI TION FLA PS
measure
(TC-2003 AND A FTER;
the
flap
travel with
a
flap
travel gage.
TE- I A ND A FTER; TH- I AND
Adjust
the
AFTER)
NOTE
Beech recommends the
use
of the
flap travel
of this manual. Place the travel gage
Four limit switches
the
flaps.
Use
a
tone for up position,
flap
travel gage to
two for
measure
the
on
flap
gage shown in the GENERAL INFORMATION section
aft of the flap actuator.
flap just
approach position and one for down position) control
travel when adjusting the limit switches.
the travel of
NOTE
Rig
the
flaps
under
simulated
a
flight
load to minimize overtravel
(coasting)
of the
flap
motor after
the ii mit switc h has bee n actu ated.
a.
Adjust
b.
Adjust the 14" (outboard) limit switch in its mounting
position to the APPROACH position.
the
uplimit switch
so
that the
flap stops
at neutral
(UP position).
slot to
stop the flap
at 14" to 14.5" after the
flap
moves
from
at 15.5" to 16" after the
flap
moves
from
the UP
c.
Adjust the 16" (inboard) limit switch in its mounting
position to the APPROACH position.
slot to stop the
flap
the DOWN
d.
Adjust
e.
Remove the bolt
f.
Turn the
g.
Install the bolt
E16
the downlimit switch in its
attaching
jackscrew
on
the
connecting
the
right
right
the
mounting
actuator to the
actuator in
right
stop the flap
slot to
or
out
right flap.
u ntil
actuator to the
at 28" to 30" of down travel.
the
rig ht flap aligns
with the left
flap.
flap.
4-75
BEECH BARON 55 AND 58 SHOP MANUAL
h.
flaps down, adj ust the rubber bu mper installed
screw i n or out as required to remove play or stop
With the
adj usti ng
on
the rib between the
vibration when the
flap
flap
and the ai I e ro n. Tu m the
is in the U P pos ition.
NOTE
A d i sti net cha nge i n the sound of the
excessive outward
adjustment
flap
mote r nea r
of the rubber
i.
Operate the flaps through their full travel. Make
the
ru bbe r
co
mpletion
of the
flap travel
can
indicate
bumper.
sure
that the
flaps
contact the limit switch befo re
they
contact
bu m per.
FLA P POSI TION INDICA TOR A DJUS TMENT (TC-350, TC-3 71, TC- I 0 I I AND AFTER; TE- 1 98
A ND A FTER; TH- I THRU TH- 1 368, TH- 1 390 THRU TH- 1 395)
NG URE 4-30
NOTE
to
i
p rior to the serials noted above used I ig hts on th e n st ru me nt panel
indicate
to
the
on
with
flaps
indicate the up and down pos it i on s i n co nj u ncti o n
stripes painted
intermediate positions. Airplanes with serials after those noted above used lights to indicate all of
Airplanes manufactures
t h e f lap po siti o ns.
An
adjustable
of the
a.
rear
Adjust
transmitter for the
flap position indicator
is installed
on
the
flap
actuator in the left
wing, just
fo rward
spar.
the
flap
limit switches to obtain the correct
flap travel (see
FLAP LIMIT SWITCH ADJUSTM ENT).
down and check the flap position indicator for the corresponding reading. If fully down flaps
loosen
the transmitter attaching bolts. Adjust the transmitter forward and aft, or rotate it slightly to
are not indicated,
the
correct
reading. Tighten the bolts attaching the transmitter.
get
b.
Run the
flaps fully
c.
Run the
flaps fully
up and check the indicator for full up
flaps (0") reading.
FLAP ACTUATOR
INDICATOR
TRANSMI~FER
TO ADJ UST, LOOSE N MOUNTING
BOLTS AND MOVE FORE AND AFT,
OR ROTATE SLIGHTLY
~II
ill
INDICATOR~ I
TC- 2003 AND AFTER
TE-768 AND AFTER
TH- 1 THRO UGH TH- 1388
TH- 1390 THRO UGH TH-1395
Flap Position
/I
TC-1 THROUGH TC-2M32
TE-1 THROUGH TE-767
5&161-15
Transmitter and indicator
Figure
4-76
ag
4-30
616
BE ECH BARON 55 AND 58 SHOP MANUAL
FLAP MO TOR A ND GEA RBOX REMO VAL
FIG URE 4-32
caunon 1
I CAUTION
The
flap motor used on airplane serials TC-2003 and after, TE- 1084 and after and TH-773 and after
interchangeable with the flap motor used on earlier airplanes.
is not
a.
Remove the cabin front seats.
b.
Remove the
c.
Remove the spar
d.
Disconnect the
access cover
(TC-I
thru
(TC-1608
cover
clamps supporting
TC-1607; TE-I
and
thru TE-942
except TE-938; TH-1 thru TH-384).
After; TE-938, TE-943 and After; TH-385 and After).
the electrical
wiring.
NOTE
A retainer has been added to the
have been
on
flap cables where they join the flap gearbox. This
production airplanes or added by Beech S e rvice Bu ileti n No. 2460.
retainer may
e.
Loosen the two set
f.
Rotate the retainers 90" to line up the
g.
Loosen the nuts
h.
Pull the
i.
Disconnect the motor electrical
j.
R e move th e fl ap mote r attac h i n g bo its a nd remove the flap motor. Airplane serials TC-1 th ro u g h TC-2002,
Zhrough TE-1083, and TH-1 through TH-772 have a ground wire attached to one of the flap motor attaching
flap
screws
in each cable retainer.
keyway with
the
the inboard side of the mounti ng
on
drive shafts from the
flap
wiring
key
slot.
I
su ppo rts.
motor shaft and retainers.
quick disconnect(s).
at the
TE-1
bolts. Remove the
ground
wire.
FLAP DRIVE CABLE CONNECTION
FIG URE 4-32
Connect the LH and RH
flap
drive cables to the
flap
drive motor
as
follows, using the illustration for component lo-
cations:
a.
I nstall t he
b.
Insert the retainer
way with the
While
c.
through
d.
far
o utb oa rd
key
e.
E16
as
far
inserting
as
through the mount support
flap motor drive shaft
slot in the
the
flap
cable
through
it will go
on
the threaded
and onto the motor shaft
and
tighten
one
portion
as
set screw
far
of the
as
flap
it will go.
cable.
Align
the retainer
key-
temporarily.
the mount support, install the inboard washer and nut. in stall the cable
keyway is just past the key slot in the retainer.
the retainer and into the motor drive shaft until the
Loosen the set
as
nut and washer
screw
that
was
tightened
in step b. Ensure that the retainer is still installed
on
the motor shaft
as
it will go and rotate the retainer 90".
Keep
inboard pressure
on
the retainer and
tighten both
retainer set
screws.
4-77
BEECH BARON 55 AND 58 SHOP MANUAL
mounting support by tightening the nuts. Tighten the inboard nut to ensure
that there is sufficient clearance between the outboard edge of the retainer and the cable housing to allow the retainer to rotate without coming into contact with he cable ho us in g. If the th readed part of the cable housing is not
long enough to install the two nuts and washers, using a die, add 5/8-24 UNEF threads until 0.88 inch thread length
is reached. Tighten the outboard nut again st the mou nting support.
f.
Secure the
drive cable to the
flap
FLAP MOTOR A ND GEA RBOX INS TA LLA TION
I CAUTION 1
flap motor used on airplane serials TC-2003 and after, TE- 1084 and after and
not interchangeable with the flap motor used on earlier airplanes.
The
is
a.
Position the
through
flap
motor and install the
through
TE-1083 and TH-1
flap
TH-773 and after
attaching bolts. Airplane serials TC-I through TC-2002, TE-1
ground wire attached to one of the flap motor attaching bolts.
motor
TH-772 have
a
I nstall the g rou nd wi re.
b.
Connect the motor electrical
at the
wiring
quick disconnect(s).
NOTE
flap cables where they join the flap gear
production airplanes or added by Beech Service Bulletin No.
A retainer has been added to the
have been
I
on
drive cables to the
c.
Connect the
d.
Install the spar
e.
Install the
f.
Install the cabin front seats.
flap
cover
(TC-1608
access cover.
(TC-1
flap
box. This retainer may
2460.
drive motor in accordance with FLAP DRIVE CABLE CONNECTION.
and After; TE-938, TE-943 and After; TH-385 and
thru TC-1607; TE-1 thru TE-942
After).
except TE-938; TH-1 th ru TH-384).
FLA P MO TOR A ND GEA RBOX DISA SSEMBL Y
(TC- I THRU TC-2002; TE- I THRU TE- 1 083; TH- 1 THRU TH- 772)
FIG URE 4-3 1
wire.
a.
Cut and
b.
Remove the two
c.
Remove the
d.
Remove the set
e.
Remove the
worm
f.
Remove the
retaining pin (24) from
remove
4-78
remove
all
safety
long
screws
screws
(26)
from the motor brush
which attach the
screw
(11),
and gear
and
cover
remove
(14),
plate (8)
housing (25)
and
the countershaft
wash er
(12),
gasket (7)
(10)
th rust washer
the control shaft
(20). Slip
to
separate
to the gear
from the
the motor and
gearbox.
housing.
gearbox.
(1 5), beari ng (1 6)
the spacer
(21)
and beari ng
and washer
cu p
(22)
(1 7).
down
enough
to
the control shaft.
E16
BEECH BARON 55 AND 58 SHOP MANUAL
FLA P MO TOR AND GEA RBOX CL EANING A ND INSPECTION
(TC-I THRU TC-2002;
a.
TE- I THRU TE- 1 083; TH- I THRU TH- 772)
Clean all gearbox parts in solvent (1 5, Cons u mab re Materials Chart, Sectio n
corroded parts. Pay particular attention to the
(9) in the sides of the gearbox.
or
b.
Inspect
the brushes
of the
(27)
flap
worm
and gear
motor for wear. The
(14)
and
original length
2)
and in s pect fo r
wheel gear
worm
wo m, c racked
and the
(19)
of the brushes is 1/2 inch
bearings
long. Apply
adhesive/sealant (58, Consu mable Materials Chart, Section 2) to the brush holder th reads befo re installing the brush
plug.
FLA P MO TOR A ND GEA RBOX A SSEMBL Y
(TC- I THRU TC-2002;
TE- 1 THRU TE- 1 083; TH- I THRU TH- 772)
FIG URE 4-3 1
a.
Install
the´•opacer (21),
washer
(22)
and shim washers
(23),
and install the control shaft
(20).
Install the
retaining
pin (24).
b.
Install the washer
c.
Install the countershaft
d.
Fill the
e.
Install the
gasket (7)
f.
Install the
long
g.
Install all
(12),
worm
(16)
and gear
and
secure
(14),
thrust washer
with the set
screw
(15), bearing (16)
and
bearing
cup
(1 7).
(11).
gearbox with lubricating grease (11, Consu mable Materials Chart, Section 2).
and
screws
cover
(8)
on
(26) through
the
gearbox
and
the motor brush
secure
with the
housing (25)
to
attaching
secure
screws.
the motor to the
gearbox.
safety wire.
FLAP MOTOR A ND GEA RBOX O VERHA UL
(TC-2003 A ND A FTER;
Overhaul of the
flap
mote r
TE- 1 084 AND AFTER; TH- 773 AND A FTER)
an d
t rans m i ss i on can be obtained
gearbox assembly
individually
from
on
these serials is
Raytheon
Aircraft Parts
n ot rec o m m e nd ed.
inventory
cou p le r and
P
(RA I D).
The mote r
and D i st ri b u ti o n
FLAP SHAFT REMO VAL
FIG URE 4-32
a.
Place the
b.
Remove the front seat assemblies.
c.
Remove the spar
airplane on jacks
and retract the
landing
gear until the inboard doors
are
open
(use the circuit breaker).
cover.
NOTE
A retainer has been added to the
have been
on
flap cables where they join the flap gearbox. This
production airplanes or added by Beech Service Bulletin No. 2460.
d.
Loosen the two set
e.
Rotate the cable retainer 90".
f.
Remove the nut
El 6
on
screws on
retainer may
each cable retainer.
the inboard side of the
mounting support.
4-79
I
BEECH BARON 55 AND 58 SHOP MAN UAL
g.
Pull the
h.
Disconnect all
i.
Remove the dust
j.
Disconnect the
k.
Pull the actuator and
flap
drive shafts from the
flap
in the
rear
shaft
housing
to the
wing
structure.
section wheel well.
actuator from the
flap
motor shafts and retainers.
the shaft
clamps securing
cover
flap
wing flap
housing
and the
out of the
wing
spar section.
wing.
2
25
4
8
r
27
6
j.iei--~-3
o
a
a
-Li
11
o"V ~1
27
3
5
26
21´•
12
20-----C;
13
14
151617
I
i 1L- 2 4
1.
Flap Motor Housing
2 Ar mat u re Beari n g
14. Worm and Gear
1 5. Thrust Washer
3. Oil Seal Collar
16 Cou nter S heft Beari ng
4. Oil Seal Washer
17.
5 Ar matu re Shaft Washer
6. Motor Housing End Plate
1 8. Thrust Washer
7. Gear
Housing Gasket
8. Cover Plate
9. Sleeve
Bearing
10. Cou nter Shaft
20.
Flap Control Shaft
21.
Spacer
L~
M)-IMI-I
22 Washer
23. Shi m Wash er
Bearing,
Housing
26. Screw
27. Brushes
Flap
Motor and Gearbox
Figure
4-80
1a
19. Worm Wheel Gear
25 Brush
12. Washer
Needle
Bearing Cup
24. Retai ning Pin
11. Set Screw
13. Counter Shaft
tj
4-31
E16
BEECH BARON 55 AND 58 SHOP MANUAL
FLAP SHAFT INSTALLA TION
FIG URE 4-32
a.
Pull the
flap
b.
Set the
flaps in
shaft and
the
housing through
the
wing
and attach the actuator to the
wing flap
and
wing
spar section.
position.
ne ut ral
NOTE
A retainer has been added to the
have been
flap
p rod uctio n ai rplan es
on
or
cables where
added
by
c.
Connect the flap drive cables to the flap drive motor in
d.
Install the clamps securing the shaft
e.
Install the dust
f.
Run the
g.
Lower the
h.
Install the
i.
Install the front seat assemblies.
in the
cover
flaps through fully
rear
to the
flap gearbox.
This retainer may
acco rdance
wing
with FLAP D R I VE CAB LE CON N ECTIO N.
structure.
section of the wheel well.
up and
gear and
landing
housing
the
they join
Be ec h Se rvi ce Bulletin No. 2460.
fully
remove
down travel to check
the
airplane
from the
flap rigging.
jacks.
s pa r cove r.
FLAP INNER FLEX SHAFT REMOVAL
FIG URE 4-32
a.
Place the
b.
Remove the front seat assemblies.
c.
Remove the spar
airplane
on
jacks
and retract the
landing gear (using
the circuit
breaker)
until the inboard door is open.
cover.
NOTE
A retainer has been added to the
have bee n
on
p rod u cti o n
d.
Loosen the two set
e.
Rotate the cable retainer 90".
f.
Remove the dust
g.
Remove the two bolts
screws on
cover
in the
holding
flap cables where they join the flap gea rbox. Th is
airplanes or added by Be ec h Service Bulletin No. 2460.
retainer may
cable retainer.
rear
of the wheel well to
gain
access
the forward end of the actuator in
to the actuator.
place.
NOTE
The fi rst cl amp which
flexibility to the
The
E16
secu res
the flex d rive to the
wing may
have to be
re move d
to allow
more
flex drive.
position transmitter may
need to be removed from the left
flap.
4-81
I
BEECH BARON 55 AND 58 SHOP MAN UAL
h.
Remove the snap
ring holding
the flex drive to the actuator.
NOTE
The re
a re
space rs under the
i.
Note how far the shaft
j.
Pull the flex inner shaft from the
protrudes past
flange
the
of the flex drive;
flange
of the
use
caution that
housing. (This
they
are
not lost.
will be used for later
installation.)
housing.
FLAP INNER FLEX SHAFT INSTALLA TION
FIG URE 4-32
a.
Lubricate the inner flex shaft with grease
b.
Install the inner flex shaft into its
(11,
Chart 1,
91-00-00).
housing.
Rotate the inner flex shaft until the key on the inner end of the shaft slides into place. (When this is accomplished
c.
the measurement noted in step i of FLAP INNER SHAFT REMOVAL should again be noted at this time.)
NOTE
A retainer has been added to the flap cables where they join the flap gearbox. This retainer may
have been on production airplanes or added by Beech Service Bulletin No. 2460.
d.
Push the
e.
Rotate the retainers 90".
f.
While
flap
holding
shafts into the
flap
motor shafts and retainers.
the retainers onto the motor shafts
as
far
as
possible, tighten the
two set
screws
in each retainer.
NOTE
Be certain the spacers
Install the
g.
flap
are
in
shaft into the actuator and install the snap
place
in the actuator.
ring.
NOTE
A screwdriver may be used to make small adjustments to the
actu ato r d oes not align with the key of the flex shaft.
h.
Secure the actuator in
place
screw
of the actuator if the slot in the
with the two bolts, washers, and nuts.
NOTE
On the left
on
4-82
flap
the shaft if it
the
position
was
transmitter will have to be installed if it
was
removed. Install the
clamp
removed.
E16
BEECH BARON 55 AND 58 SHOP MANUAL
i.
I nstall the d ust
j.
Lower the
k.
Use the circuit breaker to
cove r.
landing
gear and
remove
the
airplane
slowly cycle the flaps
from the
jacks.
to determine that
they
are
prope rly ri gged.
NOTE
Fo r correct
adj ustment
and
rigging
of the
I N D ICATOR AN D ADJ U STM ENT i n th is
flap position transmitter, refer
chapter.
to the FLAP POSITION
FLA P A CTUA TOR DISA SSEII~BL Y
NG URE 4 -33
a.
Remove the snap
b.
Tap
c.
Slide the
d.
Rem ove the
on
ring (1)
piston plug (3)
the
piston (7)
and disconnect the flexible shaft
to drive out the seals
out of the
O-ring (16)
housing (8), and
from the
(5),
(2) from
spacers
unscrew
(4
the actuator.
12)
and
the actuator
and bea ri n gs
screw
(9)
(6).
from the
piston.
housing.
NOTE
The
following step
is necessary
only if the piston plug (3)
must be
replaced
because of
damage
or
wear.
e.
Drill out the
pin (11)
and take the
piston plug
out of the
piston.
FORWARD
RETAINER
(50-361131)
‘M OUNTING
SUPPORT
OUT BOARD
r-
MOIORFLAP
SET
SCREW
L_
SET/
fl I
SCREW
KEY SLOT IN
MOTOR SHAFT
SET
OUTBOARD
NUT
SCREW
RETAINER
KEYWAY
OUI BOARD
WASHER
INBOARD INBOARD
NUT
WASHER
ENSURE THAT THERE IS SUFFICIENT CLEARANCE BETWEEN THE OUTBOARD EDGE OF THE
RETAINER AND THE CABLE HOUSING TO ALLOW
THE RETAINER TO ROTATE WITHOUT COMING
INTO CONT ACT WITH T HE HOUSING.
j
jl
INBOARD END VIEW OF
RE TA I NER
50 3 6 1 1 3 1
OUTBOARD
RE T A I NE R
END
50
VIEW OF
36 1 1 3 1
EA04B
984883AA
Flap
Drive Cable Retainer
Figure
El 6
4-32
4-83
BEECH BARON 55 AND 58 SHOP MANUAL
FLAP AC TUA TOR L UBRICA TION
FIG URE 4-33
a.
Clean all parts with solve nt
tortion and excessive
wear.
(1 5,
Cons umable Materials
Replace
the
O-ring
Chart, Section 2) and inspect for cracks, corrosion, dis-
and seals.
b.
Pack the bearings with gear lube (7, Consumable Materials Chart, Section 2). Lubricate
compound (57, Consumable Materials Chart, Section 2) before installation.
the
O-ring
with silicone
FLA P A C TUA TOR A SSEMBL Y
NG URE 4-33
CAUTION I
I cnvnoN
The
flap actuator must be assembled so that the
is installed. Be
sure
there
are no
vent hole in the
housing is
on
top when the actuator
obstructions.
If the
piston plug (3) was removed, apply retaining compound (59, Consumable Materials C ha rt, Se ction 2) to
piston plug and insert the piston plug into the piston (7). Align the holes in both parts and install the new pin
(11). Peen the pin and file the ends flush with the piston exterior. Remove the excess retaining compound from both
the inside and outside of the piston. Coat the piston plug and pin with primer (24, Consumable Materials Chart).
a.
the
new
b.
install the
c.
Pour 2/3
d.
Install
ounce
one
and insert the
e.
O-ring (10)
into the
of gear lube
of the
housing (8).
(7,
Consumable Materials
bearings (6) over the threaded
housing.
Chart),
into the threaded end
end of the actuator
screw
(9).
on
Start the
the
piston (7).
screw
into the
piston,
piston into the
Install the other
bearing (6)
and the seal
(5).
Use
approximately
100
pounds
of force to seat these parts in the
housing.
f.
Install the thick spacer (4) and the thin spacers (12), the flexible shaft (2), and the snap
100 pounds of reverse force to seat the parts against the snap ring.
ring (1)
in the
housing.
Apply approximately
g. The end play between the piston and the housing must be 0.002 to 0.010 inch. Remove the snap
the quantity of spacers (4 and 12) to obtain the correct end play. Install the snap ring.
ring
and
adjust
NOTE
A maximum of five thin spacers
h.
(12)
and maximum of
Run the actuator in and out several times to check
one
operation
thick spacer
(4)
is allowed in the
assembly.
to its full travel. Excess lubricant will be forced out
of the vent hole.
i.
4-84
Install the actuator with the vent hole up. Be
sure
there is
no
tape
or
obstruction
covering
the vent hole.
E16
BEECH BARON 55 AND 58 SHOP MANUAL
I.
4
FLEXIBLE
2.
SNAP
3.
SPACERS
4.
BEARINGS
5.
ACTUATOR
6.
PISTON
7.
HOUSING
8.
HOUSING
9.
HOUSING
SHAFT
RING
SCREW
PIVOT
BARREL
IO.
PISTON
II.
PISTON PLUG
12.
O-RING
13.
HOUSING
14.
PIN
15.
PISTON
16.
PISTON COLLAR
17.
SEAL
PLUG
END
BOLT
HOLES
INSIDE
HOLE
DIMENSION
(CONNECTS FLAP
ACTUATOR)
TO
HOLE
SHAFT
17
16
10
15
II
12
I
14
13
C94EA27B2829
Flap
Actuator
Figure
E16
4-33
4-85
SECTION
LAN DING GEAR AND
BRAKE SYSTE NI
BEECH BARON 55 AND 58 SHOP MAN UAL
B RA KE SYSTEM
FIGURE 5-1
BRAKE VVEA R L IMITS
(TC- I
THRU TC-422, EXCEP T TC-3 7 1)
by the distance between ’the steel brake disc and the outside edge of the brake
the linings when this distance is 0.250 inch. On se rials TC-1 thru TC-99
Replace
housing
applied.
the measurement is to the face of the disc outside of the lining contact area. On TC-100 thru TC-422, except TC371, the measurement is to the recessed surface at the outer edge of the disc. Replace the steel brake disc when
the thickness is 0.225 inch, measured at the thinnest section. The brake disc and wheel side must also be replaced
The brake
lining
wear
is indicated
with the brakes
when the distance between the disc teeth and wheel teeth reaches 0.040.
(TC-423
THRU TC-662, TC-664 THRU TC-978, TC-960 THRU TC-983, TC-985 THRU TC-998,
AND TC-1 002)
On serials noted above, with the brakes
the flat surface
of the brake
this distance is
housing (parallel
to the
applied, measure the distance between the brake disc and
disc) near the center of the disc face. Replace the linings when
Replace the brake dise when the thickness of the brake disc has worn to 0.310 inch, or when an irregular
surface on the face of the disc has deve loped in excess of 1/16 inch. Replace the wheel half when any of the disc
drive teeth have worn to a thickness of 0.070 inch when measured 0.100 inch from the top of the tooth.
0.187 inch.
(TC-371, TC-663, TC-979, TC-984,
A FTER; A ND TH- 1 A ND A FTER)
TC-999 AND A FTER, EXCEPT TC- 1 002; TE- I AND
On serials noted above, the brake linings should be replaced befo re the metal back plate is exposed th rou g h the
abrasive surface. This can be checked visually without disassembling the brake. The minimum allowable thickness
for the abrasive surface is 0.100 inch. The brake disc should be
replaced
when its thickness
measures
0.330 inch.
PARKING BRA KE ADJUS TI~IIENT
parking brake control in the OFF position and check the parking brake valve to make sure it is in the OFF
position. Loosen the lock nut and screw and take up slack in the actuator wire. Tighten the screw and lock nut down
on the brake actu ato r wi re. P u I I the brake co ntrol to the ON position and pump the b ra ke s to see if the peda is a re
solid. If the brake pedals are not solid, put the brakes in the OFF position and recheck the rigging.
Put the
ADJUSTING THE LINKA GE ON BRAKE MA STEP CYLINDER
The proper linkage arrangement will adjust the brake pedals to a straight up-right position. This is considered the
best adj ustment si nce it wi I I prevent the pedals from hitting the firewall in their extreme forward position. To adj ust
the
linkage
for this
position loosen the jam nut on the upper end of the
length. After both pistons are adjusted to the
rod to attain the desired
cylinder piston rod and turn the piston
length tighten the jam nuts.
master
same
BLEEDING THE BRAKE SYSTEM
only hyd ra u lic fl u i d (1 3, Con su mable Materials Chart, Section 2) in the b rake I i nes and insure that no dirt or
foreign matter is allowed to get in the brake system. Dirt can get under seals and cause leaks or clog the compensating valve and cause the brakes to lock.
Use
gravity flow or pressure bleeding to bleed brakes. Using either method, the parking brake lever
pedals mu st both be fully released to open the compensating pc rt i n the brake maste r cyli nde rs.
Use either
brake
E17
and toe
5-1
I
B E EC H BARON 55 AND 58 SHOP MAN UAL
From reservoir
*Anvil
lining
Anvil aide
carrier
t´•
UI~
Tobl;L´•
master
liningPiston
i~li
~90,´•
a
cylinder
nlec
lining
Y/
Piston
cllp~
i~ip
Inlet
Brake
housing
DETAIL A
’d
BP
B
Aircraft aerial prior to
except TC-371
ii
~llet
aide
TC-423,
*Lnetalled with replacement lining
i
on some
airc raft.
DETAIL B
BRAKE
Anvil side lining
BLEEDING
r Piston side
lining
~X
i
1
‘-S,´•
Diac
I
Brake houa?ng
Source of compressed air
Aircraft serial TC-423 thru TC-662, TC664 thru TC-978, TC- 980 thru 7’C-g83,
TC-ga5 thru TC-998 and TC-1002.
Lining
~9--
ii~ i
Torque mate
I Y/
Insulator
Dtsr.
~ni
I
Pressure Plate
---z~----
t~b
mston
Shtm
Cylinders
Aircraft serial
´•;L
C
k,
TC-371, TC-663, TC-979,
TC- 984, TC- 999
TE:-I a~id sIt~r.
a
nd after
DF:’I’AIL C
except TC:-1002.
rHose
4917s3aa
B ra ke
System
Figure 5-1
5-2
El 7
BEECH BARON 55 AND 58 SHOP MANUAL
GRA VI TY BL EEDING
The reservoir must be
inate
trapped
The brake
kept full du ring bleeding.
air in the master
cylinders.
When
no more
pedals should be ope rated slowly and smoothly to elimair bubbles appear in the fluid drained from the bleeder plug,
close the bleeder valve.
PRESS URE BL EEDING
Connect the hoses from
a pressure pot to the bleeder fitting on the brake and bleed the system from the wheel cylinder up. Disconnect the fluid supply line at the reservoir, attach a hose to it and put the other end of the hose in a
large, clean container. Using not more than 30 pounds pressure, bleed the system until all air bubbles are gone from
the
draining
fluid.
Pumping
the brakes is not necessary.
BLEEDING DUAL BRA KE S YS TEM
In
airplanes having
the
optional
dual brake system, the
copilot’s brake system
is bled
by closing
the valve
pressure pot and pumping the copilot’s brake pedal to change the shuttle valve position. This causes
to be routed through the copilot’s system and this system should be bled as was the p i lot’s syste m.
Afterthe
pilot’s
and
copilot’s
on
the
hydraulic fluid
brakes have been bled, close the bleeder valve and repeat for the other wheel.
RE~O VING THE WHEEL AND BRAKE ASSEI~IBL Y (GOOD YEAR) (TC- I THRU TC-370,
TC-372 THRU TC-662, TC-664 THRU TC-978, TC-980 THRU TC-983, TC-985 THRU TC-998
AND TC- 1 002)
a.
Place
b.
Remove the cotter
airplane
on a
disc to prevent it from
jack.
pin, wheel retaining nut, spacers, bearings, wheel and release
dropping and striking the axle when the wheel is removed.
Disconnect the brake
c.
hydraulic line,
remove
the six brake
housing attaching
disc
bolts and
clips. Support
remove
the brake
the brake hous-
ing.
INSTALLING THE WHEEL AND BRAKE ASSEII~BL Y
(GOODYEAR) (TC-I
THRU TC-370,
TC-372 THRU TC-662, TC-664 THRU TC-978, TC-980 THRU TC-983, TC-985 THRU TC-998
AND TC- 1002)
Place the brake
a.
so
that the brake
housing on the axle and position the housing on the
cylinders slant down and aft from the strut center line.
b.
I nstall t h e b ra ke
housing attaching
c.
Clean the wheel
bearings with solvent(l5,
2).
bolts and connect the brake
axle
hydraulic
attaching
hole from the
line to the b rake
Consumable Materials Chart, Section
2)
and
asse
perpendicular
mbly.
repack with
grease
(9,
Consumable Materials Chart, Section
d.
Position the brake disc and install the wheel
sponding
notches in the wheel. Install the
the wheel
e.
Tighten
f.
I n stall t he wh ee I reta i n i ng
g.
Bleed the brake
517
retaining nut,
n ut
assembly, aligning the square notches in the disc teeth
bearings, spacers, wheel retaining nut, and b rake d isc c I i ps.
with
corre-
then back off until the wheel rotates.
cotte r
pi n.
syste m.
5-3
I
BEECH BARON 55 AND 58 SHOP MAN UAL
REMO VING THE WHEEL AND BRAKE ASSEIVIBL Y (CLEVELAND)
(TC-371, TC-663, TC-9 79,
TC-984, TC-999 A ND A FTER, EXCEPT TC- 1 002; AND TE- 1 A ND A FTER)
I
a.
Place the
b.
Remove the four bolts
to the
c.
airplane
then
cylinders,
on a
jack.
(six bolts
remove
D isco n n ect the b ra ke
on
the back
heavy duty brakes)
plate assembly.
the
hydraulic line,
and
remove
the
which attach the back brake
cyli nde r assembly by sliding
plate
and inner
the two g uide
pins
linings
out of the
torq ue plate.
d.
Remove the cotter
pin,
wheel
retaining nut,
spacers, and
Slide the wheel off the axle.
bearing.
The brake disc assembly can be removed, if desired, by removing the six bolts which join the wheel halves.
However, the tires should first be completely deflated.
e.
NOTE
The b rake I i n i ngs and
steps
a,
b, and
cyl i n de r
asse mb
ly
can
be
rem oved
with o ut
re movi n g
the
wheel, by utilizing
c.
INSTALLING THE WHEEL AND BRAKEASSEMBL Y (CLEVELAND)
(TC-371, TC-663, TC-979,
TC-984, TC-999 A ND A FTER, EXCEPT TC- 1002; AND TE-I A ND A FTER)
I
a.
Clean the wheel
bearings
with solvent
(15,
Consumable Materials Chart, Section 2) and repack with grease (9,
damaged grease seals, and be sure grease seal retaining
Consumable Materials Chart, Section 2). Replace any
rings are in place before installing the wheel.
NOTE
Lightly
I
felt oil
b.
saturate the felt oil seal with oil
(38, Consumable Materials Chart, Section 2). Remove the
by lightly compressing the felt oil seal sides. Coat the sides and the outer diameter of the
seal with wheel bearing grease.
excess
oil
Slide the wheel
on
the axle; and install the
bearings,
spacers, and wheel
retaining
nut.
NOTE
If the torque plate has been removed, it should be installed so that the guide pin holes
aft, and are centered above and below the horizontal center line of the axle.
c.
Install the brake
d.
Install the back
cylinder assembly by inserting
plate (inner lining) assembly,
the two
and
guide pins
tighten
the four
into the
attaching
are
positioned
the
heavy duty brake).
torque plate.
bolts
(six
on
NOTE
On the Cleveland
e.
Connect the brake
f.
Tighten
5-4
the wheel
heavy duty brakes, torque
hydraulic
the six back
plate
attach bolts to 80 to 90
inch-pounds.
line.
retaining nut,
then back off until the wheel rotates
freely
and there is
no
side motion.
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
g.
Install
h.
Bleed the brake syste m.
a new
wheel
retaining
nut and cotter
pin.
CLEVELAND BRAKE L INING REI~O VA L
On all aircraft which have the CLEV ELAN D brake
assembly, the lining, after extended use, has a tendency to stick
retaining plate. The locating pins for the lining section are peened into the retaining plate. (See Figure 5-2 or
5-3.) It is not necessary to drill out these locating pins to remove the brake lining. To remove the lining apply a screwdriver or a similar prying tool between the retaining plate and the lining, the lining should then pop off. Replace the
lining by fitting a new lining section over the locating pins in the retainer plate.
to the
I.
Cylinder
Piston
O’’ Ring
4.
Inslllalor
5.
Prc´•ssllrL´• Plate
Back Pl;lte
17
Assembly
Assembly
Back Pl;lle
7.
Shim
X.
Lining
9.
Boil
I
i
\e
18
9
I
i
o
13;/
´•h~W/
o
I
P/p’
3
3
i
O
10
10.
bolt
I I.
Sc:l 1. I~lectlsl´•
Ki nL:
12.
~0"
13.
Sc: tew,
14.
Cap.
t3lcc´•c]cr
Hlccdor
~-itling
King
’Tol-quc l’lale Al~smblp
13ushing
’I’uhe
12
Q~L/
O’’
7
17.
1X.
11
13
14
E55-21H-I
C levela n d Sta n dard B ra ke Assem bly
Figure
E17
5-2
5-5
BEECH BARON 55 AND 58 SHOP MAN UAL
2
13’i
5
3
O
J~Y10
7
1
I((
c
1U
g
\8
o~
1?
/Y)T~
Ij
17
sB
16
15
o~" ~S
14
V
6
18
ss-?ls-lo
I.
CylindL´•l´•
10.
Piston
II.
Friction King
In~ulalor
12.
Bell
13.
W;ishci
.s~
Prc´•isure PI;IIC
14.
h.
B;le k
15.
3.
7.
’’0‘’
H.
Shim
Assc´•mbly
Assembly
King
H;LCk I)I;IIU
Anchor
Ulccdcl´•
Sc l´•e w. H ]C cde r
Ih.
’’O’’ King
17.
Sc; ii. Blc´•cJcl´•
IX.
Cleveland
Bol~
Plate
As~cmbly
Heavy Duty Brake Assembly
Figure 5-3
WHEEL AND TIREREPAIR
Smooth wheel abrasions, nicks and burrs with
quer to prevent corrosion.
ce ss ive wea r.
In service, tire
so
the re is
no
Replace
any
a
fine file and retouch with zinc chromate
damaged wheel parts. Replace
tire
primer and aluminum laccasings showing breaks, blisters, or ex-
grow slightly due to shock loads in landing. Normally, this growth is balanced by tread wear
increase in tire diameter. Raytheon Aircraft Company cannot recommend the use of recapped ti res
carcasses
the Baron models. The tires may pass the retraction test when first installed; however,
tendency to swell after use and may cau se malfu nctio n of the retract system or damage the
on
recapped tires have
landing gear doors.
a
REMO VING A ND INS TA LL ING THE BRAKE hllA S TER CYLINDERS
a.
C lose pa rki n g brake valve
b.
Unsnap
5-6
the floor mat and
by pulling parking
remove
brake handle.
the floorboard section below the brake
pedals.
E17
B E ECH BARON 55 AND 58 SHOP MAN UAL
c.
Disconnect the two brake
hydraulic
lines at each master
cylinder
and mark the lines to
assure
correct instal-
lation.
d.
Remove the maste r cy I i n d e r attach i n g bolts and nuts and
e.
If
f.
Install the master
g.
Replenish
new
master
cylinders
are
to be
installed,
cylinders by reversing
and b leed the b rake
note the
the
re move
positions of
re moval
the maste r
the master
cyl i n de rs.
cylinder 45-degree
elbow
fittings.
procedure.
hyd rau lic syste m.
BRAKE IMA S TER CYLINDER O VERHA UL
PARAMOUNT
FIG URE 5-4
1
DISA SSEMBL Y
a.
Remove the snap
ring (3)
and
pull
the
piston assembly from the housing (18).
b.
Remove the clevis
(4),
rod
c.
Remove the
d.
Remove the cotter
e.
The valve
f.
Clean all parts with solvent
g.
Check all parts for cracks, corrosion, distortion and
(1 nut (2) and cotter pin (1 1 from rod (16); this will allow the
wiper (5), guide bushing (6) and O-rings (7 and 8) from the piston rod.
piston (1 0)
and
pin (12)
assembly (13)
O-ring (9)
from p i sto n rod and
from valve stop
and
spring (17)
(1 5,
(14)
and
remove
remove
will fall free of the
the
spring
re moval
washer
of retain i n g
was he rs
(1 5).
the valve stop from the p i sto n rod.
housing (18)
Consu mable Materials Chart, Section
with the
piston assembly
removed.
2).
1
wear.
ASSEMBLY
a.
Lubricate all parts with
hydraulic
fluid
(13, Consumable Materials Chart, Section 2).
NOTE
During assembly, install
b.
Install the valve
c.
Install the valve stop
d.
Install the
spring washer (15), O-ring (9)
e.
Install the
O-rings (7 and 8), guide bushing (6),
piston rod (16).
clevis
f.
E17
(1)
assembly (13)
(14)
and
spring (17)
and cotter
pin (12)
and
new
washers and seals.
into the hou si ng
to the
piston
piston (16)
rod
rod
(1 8).
(16).
to the
piston
rod
wiper (5), retaining
(16).
washer
(4),
cotter
pin (11),
nut
(2)
and
to the
Installthe assembled
piston assembly
into the
housing (18)
and install the snap
ring (3).
5-7
craft
I:’
B E EC H BARON 55 AN D 58 SHOP MAN UAL
IZ
I_
--1
17 6
--13
---12
9
1
d+--´•--l
~------7
9~--8
i
~;+--------54
B
~i23-?21,
PARAMOUNT
GERDES
1
Clevis
10.
Piston
1
Clevis
2
Nut
11
Cotter Pin
2
Lock Nut
10.
3
Snap Ring
12.
Cotter Pin
3.
Shaft
11.
4
Retaining
4
Rod
Snap Ring
O-Ring
Cap End
Bearing
O-Ring
Snap Ring
12.
5.
6
7.
8
9
(Modified)
Assembly
Stop
13.
Valve
Wiper
Guide Bushings
14.
Valve
15.
Spring
O-Ring
O-Ring
O-Ring
16.
Piston Rod
17.
Spring
Housing
Washers
18
Washer
6.
7
8
Brake Master
Figure
5-8
5
9
Collar
Spacer
O-Ring
O-Ring
13.
Piston
14.
Spring
Snap Ring
Spring
Housing
15.
16
17
Cylinders
5-4
E17
BEECH BARON 55 AND 58 SHOP MANUAL
GERDES
1
FIGURE 5-4
DISA SSEMBL Y
a.
ring (4)
Remove the snap
from the clevis end of
housing (17)
pull
and
the assembled
piston assembly fromthe
housing.
(1), lock
and cap end and
(2),
bearing (6)
from shaft
b.
Remove the clevis
c.
Remove
d.
Remove snap
e.
Remove
f.
Remove snap
g.
Remove
piston (13) from
shaft.
h.
Remove
O-ring (12)
from
piston.
i.
Remove
spring (16)
from
housing.
j.
Clean all
parts with solvent (15, Consumable Materials Chart, Section 2).
k.
Check all parts for cracks, corrosion, distortion and
O-rings (5
7)
and
ring (8),
nut
from cap end and
thrust collar
and
(9)
(3).
bearing.
spacer(l0)
from shaft.
O-ring (Il)from shaft.
ring (15)
and
spring (14)
from shaft.
1
wear.
ASSEMBLY
a.
Lubricate all parts with
hydraulic
fluid
(13,
Consumable Materials Chart, Section
2).
1
NOTE
During assembly,
Install
spring (16)
c.
Install
O-ring (12) onpiston(l3).
d.
Install
piston (13)
e.
Install
O-ring (Il)on
f.
Install spacer
g.
Install
h.
Install cap end and
i.
Install assembled
j.
Install snap
E17
into
(10),
O-rings (5
shaft
shaft.
7)
(9)
bearing,
to
and snap
ring (8)
to cap end and bea ri n g
locknut
piston assembly
ring (4)
washers and seals.
(3).
thrust collar
and
new
housing (17).
b.
on
install
(2)
into
on
shaft.
(6).
and clevis
(l)to
shaft.
housing.
housing.
5-9
BEECH BARON 55 AND 58 SHOP MANUAL
PA RKING BRAKE VAL VE O VERHA UL
NG URE 5-5
a.
Remove the valve seat
b.
Remove the elbow
c.
Remove the
d.
Remove the lock washer
(2)
(1)
spring (3), washer (4)
push
e.
Remove the old
f.
Clean all parts i n solvent
g.
Place
h.
Check the valve seat for
pi
u nge r
a new
(6)
O-ring
(9)
th rough
O-ring
parking brake valve assembly.
from the valve seat.
and
the
from the
and ball
(5)
from the valve seat.
from the
pin through the brake valve handle, remove
housing and out through the valve seat bore.
from the inside of the brake valve
wear
va lye
(7)
on
the
arm
housing.
(1 5, Con su mab le Materials Chart, Section 2)
inside the b ra ke
the spacers
and air d ry all parts.
housing.
and distortion. If necessary
replace the valve
seat.
C heck the pa rki n g b rake valve fo r I eaks by placing 1 ,500 pou nds pressure in the valve through the e I b ow (2). R emove the pressure and place it i n the nozzle (8). The valve should open with application of 2 pou nds pressure or
less. If this is not the case, the valve is not serviceable.
cJ
i~i
43
b
1
6
i. Valve Seat
2. Elbow
3. Spring
4.
5.
6.
7.
8.
9.
10.
Washer
Ball
Plunger
Spacers
Netsle
Lock Washers
O Ring
THOSE
9917J4AA
Parking Bra ke Valve
Figure 5-5
5-10
517
BEECH BARON 55 AND 58 SHOP MANUAL
LANDING GEA R S YS TEIVI
NG URE 5-6
1
I CAUTION 1
Under no circumstance should the landing gear be operated electrically while the hand crank is engaged. In the event of such an operation, a tear down and magnetic inspection should be performed
for damage to engagement slot in worm gear. (See item 1 9, Figure 5- 15.)
LANDING GEAR SAFETY SYSTEM
1
(OPTIONAL)
optional landing gear safety system functions through the action of a solenoid in the landing gear position switch
conjunction with a three position safety system switch, a relay and diode mounted on the front spar, two pressure
switches mounted on the inboard side of the left main landing gear wheel well and a micro-switch located adjacent
to each existing throttle position warning switch.
The
in
Each pressure switch is connected into the pitot and static system. The pressure switch in the gear-up circuit is actuated by the pressure differential that exists between the pitot and static ai r syste m and will close with increasing
pressure at approximately 70 mph. The pressure switch in the gear-down circuit will close with decreasing pressure
at 120
mph.
landing gear position switch is in the UP position and an airspeed of 70 mph has been attained, the presswitch in the gear-up circuit closes and actuates a relay mounted on the front spar, thus completing the circuit
and retracting the landing gear. A diode locks the relay in the closed position until the retraction cycle is completed.
When the
sure
For the
preceding
to occur however
one
micro-switch
adjacent
to the throttle
position warning
switch
mu st
also be
in the open position. Th is mic re-switch is actuated by the th rottle control when the throttle is advanced sufficiently
for the manifold pressure gage to register approximately 19 inches Hg. Conversely, if both throttles are retarded be-
approximately 1 7 inches Hg of manifold pressure, the m ic re-switches wi II close.
airspeed has dropped below 120 mph, the resultant pressure diffe re ntial betwee n the pitot and static systems wi II actu ate the pressure switch i n the gear-down ci rcu it. With both
micro-switches and pressure switches closed, the current flow through the solenoid will cause the landing gear position switch to drop into the DOWN position, thus completing the gear-down circuit.
yond
the
If at the
position corresponding
same
to
time the micro-switches close the
ON
landing gear positio n switch is placed i n the U P position while the landing gear safety system
position, the landing gear will retract only when the following conditions are mutually fulfilled.
a.
The
b.
One th rottle setti ng must have been advanced
If the
mately
By
the
airplane
19 inches
same
must have attained
an
airspeed
sufficiently
mph.
to have
produced
a
manifold p ressu re of app roxi-
Hg.
token, the landing gear will automatically extend under the following conditions:
a.
The ai rs pee d
b.
Both throttles must have been retarded
inches
of at least 70
switch is in the
m u st
h ave d ro p pe d be low 1 20
mph.
enough for manifold pressure
to have
dropped
below
approximately
17
Hg.
safety system switch is a three position switch, with no rmally ON and OFF positions. The switch also contains
momentary or test position for checking that the system is fu nctioning properly. When released from the test position, the switch returns to the ON position.
The
a
E17
5-11
BEECH BARON 55 AND 58 SHOP MANUAL
ri~´•
´•s
i:i:iiiiiiiiii;:;-
1--1
1_
L1
B~´•´•’,il
1
A R IN B b A R D
MA i N G~E
DOOR ADJUSTMENT
::~::::i:i
NOSE WHEEL TRAVEL STOP
i´•i
´•’’--i:´•´•i´•:
C
;i
MAIN ~GEAAOUTBOARD
DOOR ADJUSTMENT
i::
i :i:
1:.
i:i_
´•I
:h--:-i
i
:::i
ii i ii:::
ii
i
_
i:i i
i’:
H
NOSE WHEEL SHIMMY DAMPENER
i
ii´•;;;lii-:ii :i:l:;ili:iiiii;l;i::;l;i,
ii
i -i i:´•
´•lii:-iii:; ii::
I
O
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ii:
iiiiiii:::: i i i ::li :i:i i ::i´•;--;::i:i´•´•ii i´•;ii:;;´•
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i i --:-iii:-´•;´•;:. ::´•´•´•´•:´•-::iiii i:;;_;:a-:´•:i;;,: i´•:i:;:!´•´•i´•.i;l i
:;:i::-::::::::::
:iii:i::::-
I
i
"a
NOSE GEAR DOOR ADJUSTMENT
c´•´•l
C
.010
:i i
I
E
CHECKING MAIN GEAR DOWN LOCK TENSION
i
i
i
i-
´•ii i ii:i
-:;i;
i;
ii. iiil
MAIN GEAR UP;LOCK
i. UP LOCK ROLLER
1 UP LOCK ILOCK
SAFETYSVYITCH ADJUSTMENT
sS-nao-1
Landing Gear System
Figure 5-6
5-12
E17
BEECH BARON 55 AND 58 SHOP MANUAL
SYSTEM MAINTENANCE AND ADJ USTMENT
required for the landing gear safety system, other than replacing defective units or checking the
wiring for condition, security of attachment, and tightness of electrical connections. The switches are preset and adjustment will not normally be required; however, should the system fail to function properly, the following
checks and adjustments may be accomplished.
No maintenance is
electrical
CHECK OF SYSTEM WITH SAFETY SWITCH IN TEST POSITION
a.
Place the throttles in the closed
b.
Place the
or
retarded
master switch ON. The
battery
position.
gear circuit breaker may be either in
landing
or
out.
landing gear safety system switch in the momentary full up (TEST) position. Noise or movement of
landing gear position switch indicates that the automatic landing gear extension part of the system is fu nction i n g properly. The ON-OFF switch returns no rmally to the ON position unless the pilot intentionally
places the switch in the OFF position.
c.
Place the
the solenoid in the
MICR OSWITCH ADJ USTM E NT
gear safety system micro-switches are set to operate at 3 to 5 i nc hes Hg above the th rottle warning
horn switch (see this section for proper setting of the Throttle Warning Horn Switch). This is accomplished by a step
landing
The
in the
cam
which
operates the throttle warning horn switch.
PRE SSURE SWITCH ADJU STME NT
The pressure switches are preset and will not normally require adjustment. Because of the built-in tolerance of these
switches, they should not be tampered with unless radically out of adjustment, that is unless the switch in question
fai is to actuate at
plumbing
an
ai rspeed with in 2
and electrical
wiring
mph
above
or
below the
setting recommended for
should be checked to ascertain that the
source
it. Even then the system
something other than
of trouble is not
imprope r adj ustment of the pressu re switches.
jacks.
a.
Place the
b.
With the master switch ON, the
airplane
on
advance the throttles to maximum
landing gear circuit
position.
c.
Place the
landing
gear
safety position
d.
Place the
landing
gear
position
e.
Clamp
a
section of soft rubber
switch in the ON
switch in the UP
tubing
breaker on, and the
over
the
landing gear warning circuit breaker off,
position.
position.
pitot
head inlet,
making
certain that the connection is
Crimp the end of the tubing and roll it up until the airspeed indicator registers
retracting immediately if the pressure switch is properly adjusted.
f.
70
mph.
The
landing
airtight.
gear will start
NOTE
place the airplane o n jac ks and sta rt t h e retraction cycle
Apply a sharp load by hand in an aft di rection again st the
enough
main
If
this
the
strut.
causes
nose gear
gear wheels to move approximately 1/2 to 1 inch, it is a good
actuator
the
indication that
assembly needs overhaul and/or internal adjustment.
landing gear
Before sta rti n g t he
rigging
p roced u re,
to break the down lock tension.
E17
5-13
BEECH BARON 55 AND 58 SHOP MAN UAL
CAUTION I
I CAUTION
To avoid
rupturing
the
diaphragm
of the
airspeed indicator,
the rubber
tubing
must be rolled
If the landing gear failed to retract in the preceding step, turn the master switch OFF and
g.
switch (outboard switch of the two installed in the left main wheel well) as follows:
1.
Secure the rolled up
2.
Connect
a
tubing
so
that it will hold the
airspeed
indicator
reading
continuity tester across the contacts of the pressure switch,
reading on the airspeed indicator.
at 70
slowly.
adj ust the p ressu re
mph.
then turn the
adjustment
screw
until
the switch closes atthe 70 mph
h.
Turn the master switch ON; roll up the rubber tubing until the
so that the airspeed indicator will hold that reading.
the
tubing
i.
Retard the th rottles.
airspeed
Slowly bleed off pressure until the airspeed indicator registers
mediately if the pressure switch is properly adjusted.
j.
120
indicator
mph.
k.
Should the landing gear fail to extend, tum the master switch OFF and
switch of the two installed in the left main gear wheel well) as follows:
1.
Secure the rolled up
2.
Connect
a
tubing
so
that it will hold the
The
registers
landing
adjust
130
mph;
continuity tester across the contacts of the pressure switch, then
mph reading on the airspeed indicator.
secure
gear will extend im-
the pressure switch
airspeed indicator reading
then
at 120
turn the
(inboard
mph.
adjustment
screw
until
the switch closes atthe 120
i.
Turn the master switch ON and check the
RIGGING THE LA NDING GEAR
I
landing
(PRIOR
gear
safety system through
the
TO TC- 1 72 1; TE-990; AND
complete cycle of operation.
TH-493)
NG URE 5-6
WARNING
IwnRNINal
To
prevent possible injury, the emergency landing gear
disengaged
Before
when
operating
the gear
actuator handcrank must
always
be
electrically.
rigging procedure, place the airplane on jacks and start the retraction cycle enough to break the
Apply a sharp load by hand in an aft direction against the nose gear strut. If the main gear wheels
move approximately 1/2 to 1 inch, it is a good indication that the landing gea r actu ato r asse m b ly needs overhaul
andlo r adj u st ment.
starting
the
downlock tension.
I
I
Prior to
does not exist. Fuel should be
distributed
which could
to be
5-14
CAUTION
cAUmON
jacking the airplane, ens ure tha t an unba lanced condition
evenly in both wings to prevent an unbalanced condition
unstable while on jacks.
cause
the
airplane
E17
BEECH BARON 55 AND 58 SHOP MANUAL
NOTE
Beech Kit No. 55-8007-1S, Positive Down Lock Mechanism, is available for airplane serials TC-251,
TC-344 and TC-355 thru TC-1 720 (except TC-1 402), TE-1 thru TE-989 and TH-1 thru TH-492.
I
Beech Kit No. 55-8007-3S, Positive Down Lock M ec han is m, is available fo r ai rplane se ri als TC 1
thru TC-354 (except TC-251 and TC-344). The landing gear rigging procedures for those airplanes
having complied
with Beech Service Instructions No. 0724-211, and installation of the afore
in RIGG ING TH E LAN DING G EAR
tioned kits, will be the same as
after; and TH-493 and after).
(TC-1
721 and
men-
after; TE-990 and
Wheneve r the land in g gea r mec ha n i s m or doo rs a re re moved or disconnected, retract the gear and check the rigging. The following procedure for rigging the landing gear was written on the assumption that the entire landing gear
is out of ri g.
CAUTION 1
I CAUTION
Overtightening
or
the nut
on
the bolt that connects the retract rod to the shock strut
distort the retract rod attach
landing gear ope rations, tests and
volts under load.
All
points
on
the strut.
adjustments
are
Torque
the nut
only
to 25
to be made with a reg u lated
75
can
bind the strut
inch-pounds.
voltage
sou rce
of 28.25 ~0.25
Lengthen the main and nose gear retract rods sufficiently to eliminate the danger of the V brace on the main
gear damaging the skin when the gear is retracted and excessive tensions on the nose gear retract rods. Damage
to vital parts may result if abnormal loads are applied to the retract system. By lengthening the retract rod, such danger is removed. Disconnect up lock cables at the brackets, leaving the springs attached. If the springs are disconnected, upon the retraction of the gear the up lock arm may damage the top wing skin. Place the up lock block in
the lower position.
a.
b.
by unscrewing
at
the main gear outboard door links to main strut. Remove inboard door actuator rod
from inboard rod ends and removing bolt in door bracket.
by
Disconn ect the
the upper ball
c.
d.
wheel door
linkage
atthe
attaching point
on
the door and
remove
links
joint.
Remove bolts
unscrewing
nose
attaching
Sc rew stop bolts in
(V
brace
assembly,
main
gear)
until
approximately
four
or
five threads
are
showing.
I CAUTION I
the gear electrically before the switches are reset or for the first time after resetting
the switches, run it with extreme caution to make sure the switches open the electrical circuits before the sector gear hits the internal stops in the gear box. The sector gear should not be touching
When
running
the stop when the motor stops
the sector gea r.
coasting.
Serious
damage
may result if the internal stops
are
hit
by
NOTE
To operate the landing gear control circuit breaker as a momentary switch, push it in for operating
the gear and pull it out for stopping the ope rati on. Leave the b reake r pus hed i n only long enoug h
for the gear to make the desired distance of travel.
E17
5-15
BEECH BARON 55 AND 58 SHOP MANUAL
2/3 up. Inch the gear
Using the landing gear control circuit breaker as a momentary switch, run the gear about
the hand cran k
Check
breaker.
circuit
of
the
the remaining distance to the limit switch by the mome ntary operation
is not
clearance
If
this
for
internal
preliminary settings.
stop
for 3/8 to 1/2 turn between retracted position and the
actuator
the
to
located
landing gear
adjacent
obtained adjust the landing gear up limit switch. The limit switches are
assembly under the pilot’s seat. To adjust the up limit switch, lower the landing gear 1!8 to 1/4 tum of the emergency
hand crank and adjust the switch by turning the screw in the actuator so that it just breaks the circuit. This is to pree.
vent the sector gear from
hitting the internal stops.
Extend gear electrically and check with the hand crank. There should be 1/8 to 1/4 turn between the extended
switch actuator arm
position andthe inte mal stop. The down limit switch adjustment is accomplished by bending the
f.
tab
so
that it
just
breaks the circuit.
Extend and retract the gear two or three times to
g.
crank each time to ensure proper adjustment.
assure
that the switches
are
correctly
set. Check the hand
NOTE
It may be necessary to make a closer setting of the limit switches, but there should
than 1/8 of a turn on the hand crank in either the extended or retracted positions.
never
be less
(either right or left) to maintain 1/16 inch minimum clearance between the joint (knee)
of the V brace and lift leg and the top wing skin with the landing gear fully retracted. The main gear should retract
To decrease
only far enough to clear the inboard door in addition to maintaining the minimum of 1/16 inch clearance.
increase
to
clearance,
retract
the
lengthen the
shorten
rod;
the clearance between the knee and the top wing skin,
h.
Adjust the
main retract rod
ret ract rod.
When the proper setting is obtained, leave the gears in the retracted position and screw the stop bolt down
st the bolt
d
against the main strut. To assure a firm seating, insert a 0.003 feeler gage under the bolt head an adj u
bolt down
the
screw
until a firm, steady effort is required to pull the feeler gage out. With the feeler gage removed,
i.
an
additional 3/4 turn.
Tighten
locknut
securely.
NOTE
Refer to Beech Service Instructions No. 0448-211 Rev. 1
I
Roller
Lubricating
Bolt
or
subsequent, installation of Up Lock
Assembly.
roller
Check the up lock roller for free movement and a maximum clearance of 0.010 to 0.020 inch between the
I
the
b
loosen
oc k reand the up lock block. If this clearance is n ot co rrect, th e up lock must be adjusted. To adjust,
block
the
and
taining bolts and adjust the clearance between the roller and the up lock block. The up lock bracket
are serrated and the serration must be interlocked with each other.
j.
NOTE
The up lock cable attach bolt must be installed with the head pointing aft to avoid interference with
st ri ng e r i n the main gear wheel well when the gear is fully retracted.
k.
Extend gears and attach the up lock cable to bracket.
If it
Retract the gears intermittently as in step e, above and observe the locking action of the up lock bracket.
for
tension
a
be
should
cable
The
is
cable
too
adjusted
tight.
starts to lock too soon it is an indication that the up lock
of 52-1/2 +10 -0 pounds. The tension is adjusted at the outboard end of the cable. If sufficient adjustment is not
inobtainable at the cable eye, additional adjustment may be made at No. 3 wing rib by moving the cable housing
i.
board
5-16
or
outboard.
E17
BE EC H BARON 55 AND 58 SHOP MAN UAL
m.
Exte n d t he main gear and check the force required to deflect the main gear knee joint. With the gears in down
it should take 45 to 65 pounds of force to deflect the main gear knee joint. To increase tension, add
position,
1 00 95 1 S063Y U washers between the
sion is needed,
replace
the
spring
and rod end. A maximum of five washers may be added. If
more ten-
spring.
NOTE
If unable to obtain
Wear in
the
to
adequate spring tension, check for worn bushings in the retract linkage.
lengthening the entire linkage, causing the rod end sp ring
and
i
noth
n
stack,
leaving
press
g fo r sp ring adj u stme nts N ew bushings wi I I s h o rte n the
again permitting adjustment of the spring.
bushings
has the effect of
com-
ii n kage,
With the
gear’s extended in the full down position and the wheel clearing the floor, adjust the nose gear tension
(shorten or lengthen) to obtain deflection force of 55 pounds or higher (providing the retract
does
stack
not
at any point during the full travel of the nose gear) at the union of the V brace assembly and
spring
the drag leg assembly. The deflection force should be applied at the pivot point of this union in a plane perpendicular
to th e ce nte r I i ne between these assemblies. To obtain the above requi rements, additional 1 00951 DD032XM and/
or 100951DD064XM washers may be required at the forward end of the retract rod spring. With the nose wheel in
fully retracted position (strut against bumper on V brace) and with doors disconnected, a force of 30 to 35 pounds.
applied downward at the center line of the tow pin shall be required to move the strut off the bumper. With the nose
gear in full retracted position and both doors fully rigged, a force of 20 pounds minimum applied downward at center
line of tow pin shall be required to move the strut 0.12 inch, measured along the line of force application.
n.
at the aft retract rod
U nsc rew main gear outboard door attaching link to assure the door is not damaged when retracted. Con nect
outboard door I in kage and retract gear slowly, checking to see that clearance is maintained between the door and
o.
gear. After
checking
procedure
until
a
to see that the door is not too
tight,
run
snug, firm fit is obtained when the door is
gear down and adjust
completely closed.
linkage
as
required,
continue this
Connect main gear inboard door linkage, retract gear slowly and check for clearance between door linkage and
p.
root rib. Run gear to 314 down position and adjust to maintain 1/4 inch minimum clearance between gear and inboard
door with the slack removed from the door I in kage. Continue this procedure until door will close tightly in both up
and down
fitting
position. Adjust doors by varying the length of the push-pull linkage
adjustment.
rods. Disconnect the rods at the clevis
to make this
CAUTION 1
ICAUTION
Install the main
landing gear door push
rod
attaching
bolt in the door linkage bracket with the head
to the rear. If installed wrong, the bolt may catch on the
ing damage
q.
Connect
Adjust the
nose
to the
door
landing
linkage
gear retract mechanism
and
rig
nose
door. Check
or
fuselage skin and root rib of the wing,
preventing the gear from retracting.
closely to
see
that the
right
hand aft
hinge
caus-
clears the tire.
gear doors by varying the length of the push-pull linkage rods in the nose wheel well. With the gear
retracted the doors should have a slight tension on them from the actuator rods to keep the doors from vibrating.
nose
NOTE
maintaining p ro pe r n ose gear door tension, the d rag brace assembly on TC-1 361 thru
TC-1721; TE-841 thru TE-990; TH-165 thru TH-170, and TH-178 thru TH-493 has an adjustable up
To aid in
lock
E17
pin.
5-17
BEECH BARON 55 AND 58 SHOP MAN UAL
safety switch for proper adjustment. Measure 3/4 inch down on the piston from the botcylinder and mark the piston with a piece of tape. Raise the left wheel with a small jack
compressing the shock strut, until the tape is even with the lower edge of the cylinder. Adjust the switch actuating
arm at the clevis so the switch is actuated as the tape touches the end of the cylinder. Remove the small jack from
the wheel. Pull Landing Gear Motor circuit breaker. Disconnect the left safety switch operating arm at the torque link
and position to simulate an "on-ground" position. Select "Gear Up", check for audible warning. Select "Gear Down".
Reconnect the safety switch operating arm. Repeat the process with the right landing gear safety switch.
Check the
landing
gear
tom of the left shock strut
s.
With the gear in the retracted position and the throttle closed, check the operation of the throttle warning horn.
linkage or warning horn switch have been disconnected, removed, or replaced, the th rottle linkage must
If the throttle
be
adj usted
so
that the
warning
horn switch closes when the throttle is
approximately
3/8 inch from
being fully
closed.
NOTE
only a temporary adjustment. The throttle must be set so the throttle warning hom activates
approximately 11 inches of manifold pressure. Refer to the procedure for adjustment of Throttle
Warning Horn Switch contained in this section.
This is
at
t.
Run gear up and check landing gear position indicator. To adjust the position indicator, remove the indicator
and bend the actuating wire to move the flag or bend the tab on the clamp to increase or decrease the flag
cover
travel. Set the
covering
serials TC-1608 and
in
place,
retract the gear and check the indicator
position with the gear retracted. On airplane
after; TE-938, TE-943 and after; and TH-385 and after, check the four landing position lights.
Three green lights, one for each gear, are illuminated whenever the landing gears are down and locked. A red light
illuminates any time one or all of the landing gears are in transit or in any intermediate position. All of the lights will
be
extinguished
u.
C h eck I i m it
when the gears
sw itc h
are
adj u stme nt
up and locked.
and
remove
airplane
from
jack.
RIGGING THE LA NDING GEAR
(TC- 1 72 1
I
AND A FTER; TE-990 AND AFTER; AND TH-4 93 A ND A FTER)
FIG URE 5-6
Read the entire procedure before attempting to rig the landing gear system. Physically locate each item while reading through the proced u re. When any part of the system requires rigging, it is recommended that ALL of the steps
in the rigging process be accomplished in the order shown.
I CAUTION I
Do not
change
the
position
the gear is in transit,
as
of the control switch to
this could
cause
damage
reverse
the direction of the
landing
gear while
to the retract mechanism.
rigging procedure, place the airplane on jacks and start the retraction cycle enough to break the
Apply a sharp load by hand in an aft direction against the nose gear strut. If the main gear wheels
move ap p roxi mate ly 1 /2 to 1 i nch, it is a good indication that the landing g ear act u ato r as se mb ly needs overhaul
an d/or adj u stm e nt.
Before
starting
the
downlock tension.
5-18
517
BEECH BARON 55 AND 58 SHOP MAN UAL
I
CAUTION
I
jacking the airpla ne, ensure tha t an unbalanced condition does not exis t. Fuel should be
evenly in both wings to prevent an unbalanced condition which could cause the airplane
unstable while on jacks.
Prior to
distributed
to be
Whe neve r the land i n g gear mechanism or doors are re moved o r discon nected, retract the gear and check the rigging. The following procedure for rigging the landing gear was written on the assumption that the entire landing gear
is out of
rig.
WARNING
IWARNINO)
To prevent possible injury, the emergency landing gear actuator hand crank must always be
disengaged when operating the gear electrically.
CAUTION I
I CAUTION
Battery voltage is not sufficient to properly cycle the landing gear during rigging. A 28.25 f 0.25 volt
power supply should be utilized for landing gear rigging. If an external power receptacle is not available on the airplane, jumper cables may be used between the battery and power supply. Be sure
of the polarity before making the connection.
gear motor without proper
cooling time after each extension and retraction cycle.
Excessive
operation
of the
landing
cooling
may
cause
damage
to the motor. Allow
a
short
I CAUTION 1
Over
or
Place the
a.
tightening
the nut
distort the strut
airplane
on
on
the bolt that connects the
attaching points. Torque
jacks
as
drag leg to the shock
75 inch-pounds.
strut can bind the strut
the nut to 25
indicated in Section 2.
nose gear retract rods sufficiently to eliminate the danger of the V brace on the main
damaging the skin when the gear is retracted and to prevent excessive tensions on the nose gear retract rods.
Damage to vital parts may result if abnormal loads are applied to the retract system. By lengthening the retract system. By lengthening the retract rod.
Len gthen the main and
b.
gear
Insert the retract arm/retract rod attach bolt
c.
pointing
aft.
Disconnect the up lock cables at the brackets, leaving the springs attached. If the springs are disconnected,
upon the retraction of the gear the up lock arm may damage the top wing skin. Place the up lock block in the lower
d.
position.
Len gthe n the
e.
nose
f.
Disconnect the
the
u ppe r
E17
ball
gear retract rod.
nose
wheel door
linkage
at the
attaching point
on
the door and
remove
links
by unscrewing
at
jo i nt.
5-19
BEECH BARON 55 AND 58 SHOP MANUAL
g.
Remove bolts
unscrewing
h.
attaching
the main gear outboard door links to main strut. Remove inboard door actuator rod
e nds and re movi ng bolt i n d oo r b rac ket.
by
from inboard rod
Screw stop bolts in
(V
brace
assembly,
main
gear)
until
approximately
four
or
five threads
are
showing.
CAUTION I
I cnuTlon
When
the gear electrically before the switches are reset, or for the first time after resetting
it with extreme caution to make sure the switches open the electrical circuits before the sector gear hits the internal stops in the gearbox. The sector gear should not be touching
running
the switches,
the
run
stop when the
motor stops. Serious
gear. When checking the
should stop immedia tely.
dynamic
damage may result if the internal stops are hit by the sector
brake system, actuate one of the limit switches and the motor
i.
Using the landing gear control circuit breaker (placarded LDG GR POS) as a momentary switch, run the gear
about 2/3 up. Bump the gear the remaining distance to the limit switch by the momentary operation on the circuit
breaker. Check the hand crank for 1/8 to 1/4 turn (5/8 to 3/4 turn on airplanes using new or white actuators) Between
the retracted
position and the
internal stop of the actuator.
NOTE
A
actuator may be installed on earlier airplanes as a spare. The new actuator may be identified
white epoxy paint on the upper actuator arm, and the upper and lower actuator housing. When
the new actuator is installed as a spare on earlier airplanes, the actuator should be adjusted by usnew
by
ing the 5/8 to 3/4 hand cran k tu rns remaining after the mote r has stopped. If th is clearance is not
adjust the landing gear up limit switch. The limit switches are located adjacent to the landing gea r actu ato r asse m b ly under the pilot’s se at. To adj u st the up limit switch, lower the land ing
gear 1/8 to 1/4 turn (5/8 to 3/4 turn on airplanes using new white actuators) of the emergency hand
crank and adj u st t h e switch by turning the sc rew i n or out to i nc rease or decrease travel so that it
just breaks the circuit.
obtained
Extend gear electrically and check with the hand crank. There should be 1/8 to 1/4 turn (5/8 to 3/4 on airplanes
j.
using the new or white actuators) between the extended position and the internal stop. On older models the down
limit switch is adjusted by hand forming the switch actuator arm tab. On models with the new actuator there is an
adjustment screw on the switch. Adjust the down limit switch so that it just breaks the circuit.
k.
Extend and retract the gear two or three times to assure that the switches are correctly set and the
operating correctly. Check the hand crank each time to ensure prope r adj ustme nt.
dynamic
brake is
NOTE
It may be necessary to make a closer setting of the limit switches, but there should never be less
than 1/8 of a turn (or 5/8 of a turn with the new or white actuators) on the hand crank in either the
exte n ded
I.
Adjust the
or
ret racted
main retract rod
of the V brace and lift
only far enough
positions.
(either right
or
the clearance between the knee and the top
retract rod.
5-20
left)
to maintain 1/16-inch minimum clearance between the
joint (knee)
and the top wing skin with the landing gear fully retracted. The main gear should retract
to clear the inboard door in addition to maintaining the minimum of 1/16-inch clearance. To decrease
leg
wing skin,
shorten the retract rod; to increase clearance,
lengthen
the
E17
BEECH BARON 55 AND 58 SHOP MANUAL
When the proper setting is obtained, leave the gears in the retracted position and screw the up stop bolt down
agai nst the main strut. To assure a firm seating, insert a 0.003 feeler gage underthe bolt head and adj ust the bo it
m.
until
an
a
pull the feeder
Tighten locknut securely.
firm, steady effort is required
additional 3/4 turn.
to
gage out. With the feeler gage removed,
screw
the bolt down
NOTE
Refer to Service Instructions No, 0448-21 i, Rev.l
bricating
Bolt
or
subsequent,
installation of
Up
Lock Roller Lu-
Assembly.
Check the up lock roller for free movement and a clearance of 0.010 to 0.020 inch between the roller and the
up lock block. If this clearance is not correct, the up lock must be adjusted. To adjust, loosen the block retaining blots
and adjust the clearance between the roller and the up lock block. The up lock bracket and the block are se rrated
n.
and the
se rrations
must be i nte rlocked.
Extend the gears and attach the up lock cable to the bracket.
o.
CAUTION 1
I CAUTION
The up lock cable attach bolt must be installed with the head pointing aft to
stringer in the main gear wheel well when the gear is fully retracted.
a void
interference with
the
With the mai n
p.
movement and
a
landing gear fully extended and the down lock in the locked position, check the mi le rs fo r free
clearance of 0.010 to 0.020 inch between the roller and the down lock block. If this clearance is
obtained, loosen the block retaining bolts and adjust to proper clearance. Torque the bolts to 90 100 inchpounds. Fully retract the main landing gear and repeat this procedure with the up lock in the locked position.
not
Fully extend the main landing gear and with the down lock in the locked position, check for a clearance of 0.03
q.
to 0.10 inch between the inboard ends of the down lock spring and the down lock at the point of juncture where the
down lock attaches to the strut. Add
or remove
washers
(P/N 100951DD040ZZ)
as
necessary to obtain this clear-
ance.
landing gear fully extended and the down locks engaged, adjust the down lock cable to a tension
pounds. The tension is adjusted at the outboard end of the cable. If sufficient adjustment is not obcable eye, additional adjustment may be made at No, 3 wing rib by moving the cable hous i ng in boa rd
With the main
of 52.5 +10 -0
tained at the
or
outboard.
clamp is to be repositioned, clean the threads of the cable clamp and nut. Apply a light
locking compound (52, Consumable Materials Chart, Section 2) on the cable clamp threads. Immediately after applying thread locking compound, install down lock cable and cable clamp on up lock cable. With the
gear in the down and locked position the cable clamp must maintain the clearance of 0.10 to 0.15 inch between the
cable clamp and the cable pulley. Torque cable clamp assembly to 80 90 inch-pound. After 5 7 m i n u tes to rq u e
cable clamp assembly to 89 90 inch-pounds.
s.
If the down lock cable
coat of thread
t.
Fabricate
ru bbe r
a
enough
to
pull
feeler gage from a piece of metal 0.002 inch thick by 1/2 inch wide by 1-112 inches long, a
hook made of a heavier piece of metal. (See Figure 5-7). The rubber band m u st st retc h t i g ht
spring
ban d and
a
the 0.002 inch mate rial from the torque knee contact surface when sufficient force is
landing gear fully extended and the down lock disconnected, check the main gear retract rod end
spring for minimum, compression of 0.08 inch. Insert the spring feeler gage fabricated in step t, as shown in Figure
5-7, in the knee contact surface of the main gear lift leg. Apply a force, as shown in Detail G of Figure 5-6, using a
push-pull scale. Apply the force until the torque knee contact surf ace of the loft leg releases the 0.002 spring feeler
u.
E17
I
applied.
With the main
5-21
I
BEECH BARON 55 AND 58 SHOP MAN UAL
reading on the push-pull scale should be 55 to 65 pounds. To increase tension add washer (P/N
100951S063XP) as required (maximum of 6), between spring and rod end. Check for a total minimum gap of 0.060
gage. The
inch between the
spring
coils.
lI´•
´•002 FEELER GAGE
HOOK
RUBBER BAND
53
i
´•s.,,,,,
Main Gear Deflection
Figure
I
5-7
NOTE
If proper down-tension cannot be established, install
v.
With the main
sion of 52
w.
10
0
Co n n ect th e
landing gear fully retracted and the uplock in the locked
pounds. (Take tensiometer reading on cable just inside
o utboa rd ma i n
Swivel the
nose
spring.
pos it i o n, ri g the
of cabin.)
uplock
cable to the ten-
I i n kage and mt ract th e gear slowly, checking to see that clearance is maintained
checking to see that the door is not too tight, ru n the gear down and adj ust the
between the door and gear. After
tin kage as required; continue this
x.
a new
procedure
wheel to check the
until the snug, firm fit is obtained when the door is
turning
completely
radius of the strut and for freedom of movement without
wheel travel stops to stop
rough spots. Adjust
imum travel in both directions.
nose
shimmy damper
closed.
binding
piston 1/32 inch to 1/4 inch maximum from
or
max-
With the gears extended in the full down position and wheel clearing the floor, adjust the nose gear tension at
y.
the aft retract rod (shorten or lengthen) to obtain deflection force of 55 pounds or higher (providing the retract spring
does not stack at any point during the full travel of the nose gear) at the union of the V brace assembly and the drag
leg assembly. The deflection force should be applied at the pivot point of this union in a plane perpendicular to the
center line between these assemblies. To obtain the above
requirements,
additional 100951DD032XM and/or
100951 DD064XM washers may be required at the forward end of the retract rod spring. With the nose wheel in fully
retracted position (strut against bumper on V brace) and with the doors disconnected, a force of 30 to 35 pounds
applied
5-22
downward at the center line of the tow
pin
shall be
required
to
move
the strut off the
bumper;
With the
nose
E17
BEECH BARON 55 AND 58 SHOP MANUAL
gear in fully retracted position and both doors fully rigged, a force of 20 pounds minimum applied downward at center
line of tow pin shall be required to move the strut 0.12 inch, measured along the line of force application.
Unscrew
z.
attaching
Connect outboard door
link of the main gear on the outboard door to assure the door is not damaged when retracted.
linkage and retract gear slowly, checking that clearance is maintained between the door and
gear. After checking that the door is not too tig ht, ru n gear down and adjust
cedure until a snug, firm fit is obtained when the door is completely closed.
linkage
as
required;
continue this pro-
Connect inboard door
linkage on the main gear; retract gear slowly and check for clearance between door linkand
rib.
root
Run
age
gear to 3/4-down position and adjust to mai ntai n 1 /4-inch minimum clearance between gear
and inboard door with the slack removed from the door linkage. Continue this procedure until door will close tightly
aa.
in both up and down positions. Adjust doors
at the clevis fitting to make this adjustment.
by varying
the
length
of the
push-pull linkage
rods. Disconnect the rods
CAUTION 1
I c*vno#
Install the push rod attaching bolt in the main gear door linkage bracket with the head to the rear. If
installed wrong, the bolt may catch on the fuselage skin and root rib of the wing, ca using damage
to the landing gear retract mechanism or preventing the gear from retracting.
ab. Connect
Adjust the
nose
door
linkage
and
rig
nose
door. Check
closely
to
see
that the
right-hand
aft
hinge
clears the tire.
gear doors by varying the length of the push-pull linkage rods in the nose wheel well. With the gear
the
doors
should have a slight tension on them from the actuator rods to keep the doors from vibrating.
retracted,
nose
NOTE
Proper nose gear door tension may be maintained through adjustment of the uplock pin
brace assembly.
on
the
drag
Check the
landing gear safety switch for proper adjustment. Measure 3/4 inch down on the piston from the botcylinder and mark the piston with a piece of tape. Raise the left wheel with a small jack,
compressing the shock strut, until the tape is even with the lower edge of the cylinder. Adjust the switch actuating
arm at the clevis so the switch is actuated as the tape touches the end of the cylinder. Remove the small jack from
wheel. Pull Landing Gear circuit breaker. Disconnect the left safety switch operating arm at the torque link and position to simulate an "on-g round" position. Select "Gear U p", check for audible warning. Select "Gear Down". Reconnectthe safety switch operating arm. Repeat the process with the right landing gear safety switch.
ac.
tom of the left shock strut
ad. With the
landing gear retracted, check the operation of the warning horn thorn and light on airplane serials TH1 543 and TH- 1 545 and after). For adjustment of the warning system, ref er to the th rottle warning ho m adj ustments
in this section. The horn
or horn and light should be actuated by the following conditions: 1) Throttle retarded below
warning switch setting on airplane serials TH-I thru TH-1542 and TH-1544; 2) Throttle retarded below th rotwarning switch setting and/or flaps fully extended on airplanes serials TH-1543 and TH-1545 and after.
throttle
tie
Run the gear up and check the landing gear position lights. Th ree green lig hts, one for each gear, are illu minated
whenever the landing gears are down and locked. A red light illuminates any time one or all of the landing gears are
in transit or in any intermediate position. All of the lights will be extinguished when the gears are up and locked.
ae.
af.
Rech eck limit switch
ag.
Safety
ah. On
E17
all bolts.
airplane
adjustment.
Tighten
locknuts and
remove
airplane
from
serials TH-1543, TH-1545 and after, check the
jacks.
landing gear-up-circuit throttle-interrupt
switch for
5-23
BE ECH BARON 55 AND 58 SHOP MANUAL
proper operation. Refer to the latter
the following procedures:
i.
Extend the
2.
With the throttle
landing
gear
part of this section for adjustment procedures. To check switch operation
fully
use
down.
fully closed, place
the
landing
gear switch in UP
position.
The
landing
gear should not
re-
tract.
advance throttle until
landing
3.
Slowly
4.
Wh e n ret ract io n starts, retard throttle to check
place relay (located
under RH instrument
gea r ret racts.
latching relay. Landing gear
panel) if required.
should go all the way up. Re-
MA IN LA NDING GEA R SER VICING
Service the main
gear. Refer to Section 2, SHOCK STRUTS.
landing
LUBRICATION
Lubricate the main wheel
bearings
and grease
fittings.
Refer to Section 2, LUBRICATION CHART.
MA IN LA NDING GEAR REMO VA L
removing
assembly.
When
the
gear, take
landing
airplane
jacks,
care
With the
b.
Disconnect the outboard
c.
Disconnect the inboard
d.
Unsnap
e.
Open
f.
Disconnect the
hydraulic
g.
Disconnect the
safety
h.
Remove the bolt
i.
Remove the stainless steel exhaust shield
the
landing
landing
canvas cover
the brake
retract the
landing gear until
a.
on
cylinder
orig i nal adj ustments
to prese rye the
gear door from the
the inboard door is in the
landing
fully
open
fittings
to facilitate
position.
gear strut.
gear doo r actuatin g rod at the forward door
and disconnect the
at the rod-end
uplock assembly
hinge.
from the strut.
bleed ports and pump all fluid from the system.
lines where the flexible hose connects to the
tubing
on
the
landing
gear.
switch wire.
attaching
the lift
leg
to the strut.
on
the lower surface of the
wing.
Remove the access door in the lower surface of the wing leading edge for access to the forward hinge
j.
taining nut and remove the nut. The rear strut brace hinge bolt is accessible by lowering the flap.
k.
Remove the brace
I.
Lower the mai n gear
hinge
bolts and associated hardware which attach the main gear to the front and
assembly from the ai rplane,
bei ng carefu I not to bend the
s ki n
at th e
bolt
re-
re a r s pa rs.
edge of the whee I
we II.
MA IN LA NDING GEA R INS TAL LA TION
a.
Ca ref u ily pos iti o n th e
b.
Align
the
hinge
pou nds. I nstal I
5-24
new
ma i n
I a nd i n g g ea r
bolt holes and install the
cotte r
asse m b
ly
in
place against the front
bushings, bolts,
washers and
n uts.
and
rea r s pa rs.
Torqu e
each
n ut
to 250
690 i nch-
pi ns.
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
NOTE
or 1 00951-S-032-XF washers as req u i red between the landing gear and
spars to maintain a maxim u m total clearance of 0.01 6 inch. The place me nt of
these washers at the front or rear may help align the lift leg.
Install 1 00951 -S-016-XF
the front and
rear
wing leading edge.
door in the lower
c.
Install the
d.
Install the stainless steel exhaust shield to the lower surface of the
e.
Install the bolt
access
attaching
the lift
leg
wing.
to the strut.
NOTE
Ove rtig hteni ng the nut
distort the strut
f.
Connect the
g.
Con nect th e b ra ke
h.
Connect the
landing
gear
the bolt that connects the lift
on
attaching
po i nt.
safety
hyd ra u I ic
Toro ue the
nut to 25
leg to the shock
inch-pounds.
strut can bind the strut or
75
switch wire.
I i n e.
uplock assembly
to the strut and snap the canvas cover in
place.
CAVTION t
I CAUTION
The
uplock cable
attachment bolt must be installed with the head of the bolt
stringer in
avoid interference between the bolt and the
pointing
the main gear wheel well
as
the
aft. This is to
landing gear
is retracted.
i.
Connect the inboard
j.
Install the outboard
k.
Bleed the brake.
landing
landing
gear door
actuating
gear door to the
rod to the forward door
landing
hinge.
g e a r st rut.
CAUTION
I cnvno#l
Excessive
landing gear motor.
i.
Operate
the
landing gear motor without proper cooling may ca use damage
Allow a short cooling time after each extension and retraction cycle.
operation
landing
of the
gear and check for proper
MA IN LA NDING GEA R-O VERHA UL
rigging
(TC- I
of the
uplock
to the
and doors.
THRU TC-354 EXCEP T TC-25 1 AND
TC-344)
NOTE
Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in Section 15 for time limits and maintenance checks of the main
landing gear.
Experience in the field indicates the points of greatest wear on the main landing gear are the upper and lower bearthe cylinder assembly. The wear caused to the bearin gs during takeoff, landing and taxiing tend to result in
ings in
E17
5-25
BEECH BARON 55 AND 58 SHOP MANUAL
an
oversized condition. The oversized condition of the upper bearing in the cylinder assembly will result in leakage
and O-ring. This will eventually cause fluid to seep down through the felt
hydraulic fluid through the upper bearing
pad and out the lower bearing.
of
When
replacement of the scraper ring and all O-rings in the cylinder assembly fails to stop leaks, the oversized conprobable. In such instances the landing gear should be overhauled. The following informa-
d itio n of th e bea ri n gs is
tion will aid in dete rmi n i n g the exte nt of landi ng gear
re place c ritical land ing gear co mponents.
MAIN GEAR DISASSEMB LY
(TC-1
wear
and whether it is
THRU TC-354 EXCEPT TC-251 AND
possible
to overhaul
or
necessary to
TC-344)
FIGU RE 5-8
WARNING
IWARNING)
begin
Do not
any
disassembly
of the main
landing
gear until all air pressure has been
re-
leased.
a.
Place the
b.
Release the air pressure from the
landing
gear in
a
position
vertical
prevent hydraulic fluid from spilling.
to
cylinder assembly (10) by depressing
the valve
core
in the air valve
assembly
(1).
all
hydraulic plumbing, safety
c.
To prevent
d.
Remove the main wheel and brake
damage,
remove
assembly.
switch components, and
clamps.
Refer to Section 5, REMOVING THE WHEEL AND BRAKE AS-
SEMBLY.
Remove the snap ring (3), barrel end lock (2), barrel end
push the orifice tube (11) out of the cylinder assembly (10).
e.
gear and drain the
f.
Invert the
g.
Remove the air valve
h.
Remove the
landing
hyd rau lic
and retract the lower shock
assembly (37)
to
flu id.
assembly (1) and O-ring (5) from
piston ring (16) from
plug (4)
the orifice head
the barrel end
plug (4).
(15).
WARNING
IWARNINO)
Do not disconnect the torque knees (25 and 30) without first deflating the cylinder assembly
The torque knees provide the extension stop for the lower shock assembly, and when
(10).
disconnected, the lower shock assembly is free
i.
Remove the nut, washe r, and bolt
(29) connecting
Remove the upper and lower torque knees
and 32), retaining pins and cotter pins.
j.
k.
Slide the lower shock
5-26
assembly (37)
out of
(25
to slide out of the
the upper
and
torque
30) by removing
knee
cylinder assembly.
(25)
to the lower
torque knee (30).
the upper and lower torque knee
pins (24
cylinder assembly (10).
E17
BEECH BARON 55 AND 58 SHOP MANUAL
43
~A
b
I.
3.
4.
io
5.
6.
AIR VALVE ASSEMBLY
BARREL END LOCK
SNAP RING
BARREL END
HINGE
8.
9.
I I
IO.
I~
I 3
II.
12.
13.
14
14.
15.
15
16
22
16.
17.
18.
19.
17
PISTON
I
20
24
21
25.
26
I
11
27.
=n--- 32
-r
3~
34
28.
KNEE
32.
33.
34.
35
36.
37
37.
A
UPPER TORQUE KNEE
BORE
UPPER iOROUE KNEE
PIN
UPPER TORQUE KNEE
LOWER T OR OUE KNEE
BORE
UPPER IORQUE KNEE
BORE
CENTER TOROUE KNEE
BUSHING
29.
30.
31.
36
OETAIL
RING
UPPER TORQUE
BUSHING
3 1
~1 I
BUSHING
WEL DED BRACE
CYLINDER ASSEMBLY
ORIFICE TUBE
UPPER BRAZED BEARING
ORING
FELT PAD
ORIFICE HEAD
PISTON RING
LOWER BRAZED BEARING
SCRAPER SEAL
ADAPTER RING
SNAP
23.
30
HINGE
21.
---~7,
27
ASSEMBLY
BORE
20.
18
28
PLUG
O-RIiuG
UPPER SHOCK
BOLT,
WASHER,
LOWER
TORQUE
NUT
KNEE
LOWER TORQUE KNEE
BUSHING
LOWER TORQUE KNEE
PIN
LOWER TORQUE KNEE
BORE
AXLE SOCKET
BRAZED RETAINING BOLT
AXLE
LOWER SHOCK ASSEMBLY
C95TC3280234
Main
Landing
Gear Assem bly
(TC-1
thru TC-354 except TC-251 and
5-8
TC-344)
Figure
E17
5-27
BEECH BARON 55 AND 58 SHOP MANUAL
i CAUTION 1
The scraper seal (18) may become sharp during normal operation of the gear;
ercised to avoid possible injury when removing the scraper seal.
I.
The
I
a
MAIN GEAR
ex-
landing
gear
from
m us ic
wi re. Ref er to
Figure
5-1 0.
hinge bushing (8).
CLEANING, REPLACEMENT PARTS AND REPAIRS
TC-344)
THRU TC-354 EXCEPT TC-251 AND
CLEANING
(TC-1
THRU TC-354 EXCEPT TC-251 AND
dry
Clean all parts with solvent
after cleaning.
b.
Immerse all internal
(15,
TC-344)
Consumable Materials Chart, Section
2).
Remove all
excess
solvent and
wipe
parts in clean hydraulic fluid (13, Consumable Materials Chart, Section 2) prior to assembly.
REPLA CEMENT PARTS
I
man uf actu red
hook
Rem ove the main
(TC-1
a.
should be
Remove the snap ring (20), adapter ring (19), and scraper seal (18). Remove the felt pad (14) and O-ring (13).
O-ring is located in the upper brazed bearing (13) of the cylinder assembly (10). Removal of the O-ring may be
simplified by using
m.
care
(TC- 1
THRU TC-354 EXCEPT TC-251 AND
TC-344)
FIG URE 5-8
a.
Inspect all parts and
assemblies for damage
We ar wh i ch is greater than the allowable
Damage
which cannot be corrected
Screws that
Parts that
are
are
severely damaged
cracked, chipped
Parts that have corrosion
b.
or
or
The
following conditions
are cause
for
rejection:
have
stripped, severely
worn o r sco red
th read s.
broken.
ma i n
land i n g gea r is
repaired.
ove rhau led:
pins
Felt Pad
Piston
wear.
tolerances. Refer to Chart 5-1
other defects that cannot be
Re p lace t he fo I lowi n g pa rts whe n
Cotter
wear
excessive
repaired.
or
or
or
(14)
Ring (16)
O-Rings (5, 13)
Safety
Wire
Scraper
Seal
(18)
and
Adapter Ring (19)
Snap Rings (3, 20)
c.
R ep lace the fo I I ow i ng pa rts
o n co nd iti o n w he n
main
landing
gea r i s
ove rhau I ed.
Bushings (8, 22, 28, 31)
5-28
E17
BEECH BARON 55 AND 58 SHOP MANU AL
Grease
Fittings
Grommets
Hydraulic
Hoses
Hyd rau lic Tubing
Safety
Switc h
Components
Valve Co re
Wiring
REPA IRS
(TC- I
TC-344)
THRU TC-354 EXCEPT TC-251 AND
FIG URE 5-8
1
a.
Visually inspect castings for cracks
and
wear.
cessively
b.
and
pitting;
and finished surfaces for
Refer to Chart 5-1 for tolerances to aid in
wo m
determining
scoring, pitting, nicks, cracks, distortion
wear. Replace all defective and ex-
the extent of
parts.
If fluid leaks have been observed
on
top of the air valve assembly (1), check the small O-ring of the valve; then
look for defects in the valve.
c.
(5)
d.
junction of
plug (4).
If the leak is from the
i n the ba rre I
All parts
S I ig ht
or
sco
end
assemblies may be
of sh afts may be
ring
the barrel end
plug (4) with the cylinder assembly
if any of the
repaired
cc rrected
following proble ms
by lapping carefully
with
a
walls
(10),
check the
O-ring
exist:
flat oil stone.
NOTE
Do not exceed 10% of the component material thickness when
removing nicks,
burrs and
scratches.
Smooth minor nicks, burrs, and scratches.
Those parts that
as
that removed
Minor thread
or
are
to be
scratched
replaced
damage,
or
have
with
new
chase to clean
worn
paint
may be
stripped
and
repainted
with the
same
type of paint
parts.
or
smooth.
NOTE
damage requires inspection to determine the depth of penetration and the cross-sectional a rea change. The damaged area must be th o ro u g h ly cleaned and the corrosion must be removed. The deterioration caused by corrosion or removal of corrosion must not reduce the material
thickness of any component by more than 10%. Refer to Chart 5-1 for MAIN LANDING GEAR
Corrosion
WEAR TOLERANCES AND INSPECTION PROCEDURES
tion contact the Technical
Support Department
of
on
Raytheon
components. For additional informa-
Aircraft
Company,
P.O. Box 85, Wich-
I
ita, KS 67201.
Remove corrosion if
mium
E17
plate
applicable,
per Fed QQ-P-416,
and
Type
apply
corrosion
prevention materials
as
necessary per MIL-C-5541
or
cad-
II.
5-29
BEECH BARON 55 AND 58 SHOP MANUAL
that check within allowable
Bushings
When evidence of
damage
wear
tolerances may be reused.
exists to steel parts,
magnetic particle inspect
per MIL-STD-1949.
NOTE
Do not remove paint or primer from the area to be fluorescent or dye penetrant inspected per MILSTD-6866. If the finish absorbs the penetrant so that bleed out prevents satisfactory inspection or
if a new finish has not cured for at least 30 days, contact the Technical Support Department of Ray-
I
theon Aircraft
Company,
When evidence of
P.O. Box 85, Wichita, KS 67201.
damage exists
to metal
parts other than steel, fluorescent penetrant inspect per MIL-STD-
6866, Type I.
R ep lace d ama ged
or
unserviceable parts with
MAIN GEAR ASSEM BLY
I
(TC-1
new o r se rviceab I e
parts.
TH R U TC-354 EXCE PT TC-251 AND
TC-344)
FIGURE 5-8
NOTE
Prior to
assembly,
immerse all internal parts
able Materials Chart, Section
a.
I
O-ring (13) in the upper brazed bearing (12) of
O-ring (13) into position. Refer to Figure 5-10.
10W30 oil and install in the
Soak the felt
brazed
pad (14) in SAE
bearings(l2 and 17).
felt pad
(14))
in
hydraulic
fluid
(13,
Consum-
2).
Install the
used to work
b.
(except
the
cylinder assembly (10).
cylinder assembly (10)
Two dowel rods may be
between the upper and lower
Slide the scraper seal (18), adapter ring (19) and snap ring (20) over the piston (21) and insert the lower shock
assembly (37) into the cylinder assembly (10). Work the scraper seal (18) into the lower end of the cylinder assembly
(10) until seated. Secure scraper seal (18) with adapter ring (19) and snap ring (20).
c.
I nstal I u ppe r to rq ue knee (25) to the cylinder assembly (1 0) and lower torque knee (30) to the lower shock assembly (37) using torque knee pins (24 and 32), retaining pins and cotter pins. Insert the center torque knee bushing
(28) and connect the torque knees (25 and 30) using bolt (29), washers and nut.
d.
e.
Lubricate
f.
Install
bearings
new
at grease
fittings
hinge bushings (8)
into
with g reas e
hinge
bore
(8,
Co ns u m ab I e Materials C h a rt, S ecti o n
2).
(7).
Raise and block the lower shock assembly (37) 1/4 inch from the fully compressed position and fill cylinder asmbly (10) with hydraulic fluid (1 3, Consumable Materials Chart, Section 2) until the top of piston (21 is covered
(approximately 2 pints of hydraulic fluid).
g.
se
piston ring (16) to orifice head (15) and install into the cylinder assembly (10). Slowly extend lower
assembly (37) allowing the suction to pull orifice tube (11) down into the cylinder assembly (10). Install air
valve assembly (1) into barrel end plug (4). Install O-ring (5) around the barrel end plug (4) and insert into the top of
the cylinder assembly (10). Secure barrel end plug (4) with barrel end lock (2) and snap ring (3).
h.
Assemble the
shock
5-30
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
WARNING
IWARNINOI
As with all
forming
i.
Inflate the
end
plug (4)
operations involving equipment under high pressure, exercise
test; avoid the areas directly above and below the strut.
caution when per-
the leak
cylinder assembly (10) to approximately 100 psi using dry air or nitrogen.
assembly (1) with soapsuds and check for air leaks.
Coat the
top of the barrel
and air valve
Release the air pressure; clean the
with fresh water and wipe dry.
j.
k.
Install all
I.
Install main wheel and brake
soapsuds
hydraulic plumbing, safety
off the top of the barrel end
switch components and
assembly. Refer
to Section
plug (4)
and air valve
assembly (1)
clamps.
5, INSTALLING THE WHEEL AND B RA KE ASS E M
BLY.
m.
Install main
n.
Se Nice the main
landing
gear to the
landing
airplane.
Refer to Section 5, MAIN LANDING GEAR IN STALLAT ION.
gear. Refer to Section 2, SHOCK STRUTS.
C HA RT 5-1
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-1
ITEM
THRU TC-354 EXCEPT TC-251 AND
I.D
O.D.
TC-344)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
NOTE
Listed below a re t h e to I e ra nce s used to determine the extent of wear in the main landing gea r compone nts.
Where pe rti n e nt, the permissible we ar I i m its are given fo r th ose components. A I I i n s i de-d i amete r
and
outside-diameter (O.D.) dimensions are given in inches. Refer to Figure 5-8.
Lower Shock
Assembly (37)
Visually inspect piston (21), axle (36), axle
socket (34), and b razed retain i ng bolt (35) for
wear, damage and corrosion. Any sign of
scratch es and
wo rn are as w h ic h can
not be
repaired is cause for rejection. Conduct a
mag netic-particle i nspection pe r M I L-STD-1949. Any sign of cracking is cause for
rejection.
Piston
(21)
C h ro me Portion
1 .602
1 .8635
1.593
1.8600
Vis ually i nspect for wear, da mag e and
corrosion. Replace if wear tolerances are
exceeded.
Axle
(36)
1 .498
1.497
Vis ually i nspect for wear, damage and
corrosion. Strip and cadmium plate axle
necessary, per Fed QQ-P-416,
on scratched or worn areas.
E17
Type II,
as
Class 2
5-31
1
BEECH BARON 55 AND 58 SHOP MAN UAL
CHART 5-1
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDUR ES
(TC-1
ITEM
THRU TC-354 EXCE PT TC-251 AN D
I.D
O.D.
TC-344) (CONTI NU ED)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Upper
and Lower
Knees
(25
and
Torq ue
Vis ually i ns pect for wear, damage and
corrosion. Conduct a magnetic particle
30)
inspection
per MIL-STD-1949.
cracks, scratches
Any sign
or worn areas
which
of
can
not
be
repaired is cause for rejection. Remove all
bushings and inspect bores for corrosion.
Replace bu sh ings as needed and cadmium
plate per FED QQ-P-416, Type II, Class 2.
To rq ue Knee Bore
(23
and
Visually i nspect fo r
corrosion. Replace
0.6255
33)
0.6245
wear,
if
damage
wear
and
tolerances
are
exceeded.
Bushings (22
and
31)
Visually i nspect fo r wear, damage and
corrosion. If bushings exceed wear tolerances,
replace with new bushings. Alignment ream
new bushings to specified wear tolerances.
Drill out lubricator holes through bushings and
0.501 5
0.4995
install lubricators.
Knee Pins
(24
and
32)
0.4990
0.4980
Visually inspect for wear, damage and
corrosion. Any sign of scratches or worn areas
which can not be repaired is cause for
rejection. If no visible wear is evident, conduct
mag n etic pa rt icl e i ns pectio n pe r M I L- ST D1949. Any sign of cracks is cause for rejection.
Replace if wear tolerances are exceeded.
To rq ue Knee Ce nte r H i nge
Joint
Bore
(Upper) (27)
Inspect for wear, damage and corrosion.
Replace if wear tolerances are exceeded.
0.4420
0.4370
Bushing (28)
0.31 50
0.4360
0.3120
0.4330
Visually i nspect fo r
corrosion. Replace
wear,
if
damage
wear
and
tolerances
are
exceeded.
Bore
(Lower) (26)
0.31 75
Visually inspect for
wear, dam ag e
0.3125
corrosion.
if
Replace
wear
an d
tolerances
are
exceeded.
5-32
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
C HA RT 5-1
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDUR ES
(TC-1
THR U TC-354 EXC E PT TC-251 AN D
ITEM
I.D
O.D.
TC-344) (CONTI N U E D)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
O rif i ce Tu be
(1 1
1 .560
1.557
Visually inspect for wear, damage and
corrosion. Any sign of scratches or worn areas
which can not be repaired is cause for
rejection. Check the orifice O.D. does not
exceed
wear
tolerances. Check that orifice hole
does not exceed 0.187 inch. Cadmium
head)
Upper Shock Assembly (6)
plate
as
fo r rin g groove in orifice
per Fed QQ-P-416, Type I, Class 2.
necessary
terce pt
Visually inspect the cylinder (10) and welded
brace (9) assemblies for wear, damage and
corrosion. Any sign of cracks, scratches or
worn areas which can not be repaired is cause
for rejection. If no visible wear is evident,
conduct magnetic particle inspection per MILSTD-I 949. cad mi u m p late pe r FE D QQ- P-41 6,
Type II, Class 2 and touch up paint as required.
Cyl i nder
Upper
Asse mbly
Brazed
(1 0)
Bearing (12)
1.8680
Visually inspect
1 .8645
co rrosion.
a re
Lowe r Brazed Beari ng
(1 7)
Vis ually i nspect fo r
1 .8645
corros ion.
I nst ru ct io n Placards
Hinge
Bo re
u p pe r s h ock assem bl y.
wea r,
damage
If i nte rnal beari ng
remove
inspection
wear
and
tolerances
re p lace u p pe r s h ock asse m
exceeded,
Do not
for
Welded Brace
exceeded, rep lace
1 .8680
a re
damage and
bearing wear to lerances
for wear,
If i nte rnal
from
bly.
cylinder assembly except
place me nt.
p u rpo ses o r re
(9)
(7)
0.6275
Vis ually i nspect fo r wear, d am age and
0.6245
corrosion. If
wear
tolerances
contact the Technical
are
exceeded,
Support Department of
R ayt heo n Ai re raft Co m pa ny, P.O. B ox 85,
Wichita, KS 67201.
Hinge Bushings (8)
Safety
Switch Com ponents
0.5005
0.6235
Replace bearings
0.4995
0.6220
overhauled.
when main
gear is
continuity when
Replace wiring and
Ensure there is electrical
switch is activated.
com po nents on
El 7
landing
condition.
5-33
I
B E ECH BARON 55 AN D 58 SHOP MAN UAL
MA IN LA NDING GEA R-O VERHA UL
TC-355 A ND A FTER; TE- I A ND A FTER; TH- 1 A ND A FTER)
(TC-25 1, TC-344,
NOTE
Refer to the OVERHAU L AN D REPLACEMENT SCHEDU LE in Section 1 5 for time limits and maintenance checks of the main
landing
gear.
Experience in the field indicates the points of greatest wear on the main landing gear are the upper and lower bearings in the cylinder assembly. The wear caused on the bearings during takeoff, landing and taxiing tend to result in
an ove rsized condition. The oversized condition of the upper bearing in the cylinder assembly will result in leakage
of hydraulic fluid through the upper bearing and O-ring. This will eventually cause fluid to seep down through the felt
pad and out the lower bearing.
When
replacement of the scraper ring and all O-rings in the cylinder assembly fails to stop leaks, the oversized conbearings is probable. In such instances the landing gear should be overhauled. The following informa-
dition of the
tion will aid in dete rm i ni n g the exte nt of lan d i n g gear
re place c ritical land i ng gear co mpo nents.
MAIN G EAR DISASSEMBLY
I
(TC-251 TC-344,
wear
and
TC-355 AND
w h et he r
it i s poss i ble to overhaul
AFTER; TE-1
or
necessary to
AN D AFTE R; TH-I A N D A FTE R)
F’GURE 5-9
WARNING
IWIRNINO)
Do Not
Begin Any Disassembly
Of The Main
Landing
Gear Until All Air Pressure Has Been
Released.
gear in
a.
Place the
b.
Release the air pressure from the
c.
To prevent
d.
Remove the main wheel and brake
landing
damage,
a
vertical
remove
all
position
prevent hydraulic fluid from spilling.
to
cylinder assembly (9) by depressing
hydraulic plumbing, safety
assembly.
the valve
core
switch components, and
(2).
clamps.
Refe r to Section 5, REMOVING THE WHEEL AND BRAKE AS-
SEMBLY.
e.
Remove the retainer
cylinder
asse
ring (5)
and retract the lower shock
assembly (35)
to
push
the orifice tube
(6)
out of the
mbly (9).
f.
I nve rt the land i ng gear and d rai n the
g.
Remove the air valve
hyd rau iic
fl u id.
assembly (3) O-ring (4), piston ring (8) and O-ring (7) from the orifice
tube
(6).
WARNING
IWARNIUO)
Do not disconnect the torque knees (23 and 34) without first deflating the cylinder assembly
The torque knees provide the extension stop for the lower shock assembly and when
(9).
disconnected, the shock assembly is free
h.
Remove the nut,
5-34
to slide out of the
cylinder assembly (9).
washers, and bolt (32) connecting the upper torque knee (23)
to the lower
torque knee (34).
E17
BEECH BARON 55 AND 58 SHOP MANUAL
and
Remove the upper and lower torque knees
31), retaining pins and cotter pins.
j.
Slide the lower shock
i.
assembly (35)
(23
out of the
and
34) by removing
the upper and lower torque knee
pins (21
cylinder assembly (9).
CAUTION 1
I cnuTlon
The scraper seal (27) may become sharp during normal operation of the gea~
ercised to avoid possible injury when removing the scraper seal.
Remove the scraper seal (27), felt pad (26), O-ring and retainer rings (17). The
retainers within the cylinder assembly (9). Removal of the O-ring may be s i m p I if i ed
k.
from music wire. Refer to
I.
Disconnect the columns
ings (12) from
E17
Figure
the brace
(15)
(11).
care
should be
ex-
O-ring is located between two
by using a ho o k ma n uf actu re d
5-10.
and brace
1
(11)
from the
cylinder assembly (9)
and from each other. Remove bush-
5-35
BEECH BARON 55 AND 58 SHOP MAN UAL
I.
2.
3.
4.
5.
6.
7.
8.
9.
AIR
VALVE CAP
VALVE CORE
AIR VALVE ASSEMBLY
O-RING
RETAINER RING
ORIFICE TUBE
O-RING
PISTON RING
CYLINDER
ii.
BRACE
12.
BUSHINGS
13.
14.
BUSHING
MAIN LANDING
BRACE BOLT
15.
16.
COLUMN
UPPER BEARING
17.
O-RING,
20.
21.
22.
23.
24.
25.
26.
27
4
ASSEMBLYNU1
I
18.
19.
3
b
GEAR
7
8
RETAINER RINGS
UPPER TOROUE KNEE BUSHING
io WEc? BEARING
RETAINER RING
UPPER TOROUE KNEE BORE
UPPER TORQUE KNEE PIN
STOP
UPPER TORQUE KNEE
CENTER TORQUE KNEE BUSHING
UPPER TORQUE KNEE BORE
FELI PAD
RETAINER
A
O
RING/
9
\\!O
15
i I
SCRAPER
SEAL
28.
PISTON
CHROME
PORTION)
29.
LOWER TORQUE
KNEE BUSHING
12
I
16
1’
’3--~7
18
14
14
28
15
30.
31.
32.
33.
34.
35
36.
LOWER TOROUE KNEE BORE
LOWER TORQUE KNEE PIN
BOLI. WASHERS. NUI.
LOWER TORQUE KNEE BORE
LOWER TORQUE KNEE
LOWER SHOCK ASSEMBLY
BRAZEO RETAINING BOLT
AXLE
19
’d
~4
34
a,
23
25~
’22
33
29
30
OETAIL
A
B\
36
37
35
DETAIL
Main
5-36
Landing
Gear
B
Assembly (TC-251, TC-344, TC-355
Figure 5-9
31
C95TC05B0031
and
after; TE-1 and after; TH-I and after)
E17
BEECH BARON 55 AND 58 SHOP MANUAL
.064
WI,-i
MUSIC
3/32
--cSj
I----
I´•
DOWEL
ROD
BRAZED
BEARING
O-RING
CYLINDER
DOWEL
ROD
C94TC0582194
O-Ring
Remova I and installation
Figure
1
5-10
MAIN GEAR C LEA N I N G, R E P LACE M E NT PA RTS AN D REPAIRS
(TC-251 TC-344,
CLEANING
TC-355 AND AFTER; TE-1 AND
AFTER; TH-1 AN D
(TC-251, TC-344, TC-355 AND AFTER,
A FT E R)
TE- I AND AF’I~ER; TH-1 AND
AFTER)
parts with solvent (15, Consumable Materials Chart, Section 2). Remove all
a.
Clean all
dry
after
b.
Immerse all i nternal
excess
solvent and
wipe
cleaning.
parts i n clean hyd rau lic flu id (1 3, Consu mable Materials C ha rt, Section 2) p rio r to
REPLACEMENT PARTS
(TC-251, TC-344,
TC-355 AND AFTER; TE- 1 AND AFTER; TH-1 AND
asse
mbly.
AFTER)
1
NG URE 5- 9
a.
Inspect
all parts and assemblies for
damage
Wear which is greater than the allowable
Damage
which cannot be corrected
Screws that
Parts that
are
are
severely damaged
cracked, chipped
Parts that have corrosion
b.
Rep lace
Cotter
DU
or
wear
excessive
wear.
The
following
conditions
are cause
for
rejection:
tolerances. Refer to Chart 5-2.
repaired.
have
stripped, severely
worn o r sco red
th reads.
b ro ke n.
other defects that cannot be
the followi ng parts when the main
landing
repaired.
gear is overhauled:
pins
Bushings(l2)
Pelt Pad
E17
or
or
or
or
(26)
5-37
BEECH BARON 55 AND 58 SHOP MAN UAL.
Ring (8)
Piston
O-Rings (4, 7, 17)
Rings (5, 17, 19)
Retainer
Wire
Safety
Sc rape r Seal
c.
(27)
the fol lowi ng parts
Replace
on
condition when the main
landing gear
is
ove rhau led.
Bearings(lG, 19)
Bu sh i ngs
Grease
(1 3,
1 8,
24, 29)
Fittings
Grommets
Huck Bolt and Collar
(Replace
if removed from the upper
bearing (16).)
Hyd raulic Hoses
Hyd raulic
Tub i ng
Switch
Safety
Valve Co re
Components
(2)
Wiring
REPAIRS
I
(TC-25 i, TC-344,
TC-355 AND AFTER; TE- 1 AND AFTER, TH- 1 AND
AFTER)
NG URE 5-9
a.
Visually inspect castings for cracks and pitting;
and
wear.
cessively
b.
and finished surfaces for
Refer to Chart 5-2 for tolerances to aid in
worn
determining
scoring, pitting, nicks, cracks, distortion
wear. Replace all defective and ex-
the extent of
parts.
If fluid leaks have been observed
on
top of the air valve assembly (3), check the small O-ring (4) of the valve;
then look for defects in the valve.
c.
If the leak is from the
ring (7)
d.
in the orifice tube
All parts
or
junction
(6).
of the orifice tube
assemblies may be
Slig ht scori ng of shafts may
repaired
assembly (6)
if any of the
be corrected
with the
cylinder assembly (9) walls,
following proble ms
by lapping caref ully with
a
check the 0-
exist:
flat oil stone.
NOTE
Do not exceed 16% of the component material thickness when
removing nicks,
burrs and scratch-
es.
Smooth minor nicks, burrs, and scratches.
5-38
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
as
Those parts that are scratched or have worn
or be replaced with new parts.
plating
may be
stripped
and
replated
with the
same
type of plating
that removed
Minor thread
damage,
chase to clean
or
smooth.
NOTE
Corrosion
damage requires inspection to dete rm i ne the depth of pen etration and cross-sectional
change. The damaged area must be thoroughly cleaned and the corrosion m ust be re moved.
The dete rio ratio n caused by corrosion or removal of corrosion must not reduce the material thickness of any component by mo re tha n 1 O%. Refer to Chart 5-2 fo r MA I N LANDING G EAR WEAR
area
TOLERANCES AN D INSPECTION P ROC E D U R ES
co ntact
the Techn ical Su ppo rt
Departme nt
of
on
Raytheon
components. For add ition al i nfo rmatio n
Company, P.O. Box 85, Wich ita,
Aircraft
I
KS 67201.
Remove corrosion if
mium
plate
applicable, and apply
Type II.
corrosion
prevention materials
as
necessary per MIL-C-5541
or
cad-
per Fed QQ-P-416,
Bushings
that check within allowable
When evidence of
damage
wear
tolerances may be reused.
exists to steel parts,
magnetic particle inspect
per MIL-STD-1949.
NOTE
Do not remove paint or primer from the area to be fluorescent or dye penetrant inspected per MILSTD-6866. If the fin ish abso rbs the penetrant so that bleed out prevents satisfactory inspection or
if a new finish has not cured for at least 30 days, contact the Technical Support Department of Raytheon Aircraft
When evidence of
Company,
I
P.O. Box 85, Wichita, KS 67201.
damage exists
to metal
parts other than steel, fluorescent penetrant inspect per MIL-STD-
6866, Type I.
Replace damaged
or
unserviceable parts with
MAIN GEAR ASSEMBLY
(TC-251, TC-344,
new or
serviceable parts.
TC-355 AND
AFTER;
TE-1 AN D AFTE R; TH-1 AN D
AFTER)
FIGURE 5-9
1
NOTE
Prior to
assembly,
immerse all internal parts
able Materials Chart, Section
Install the
a.
(except
felt
pad (26))
in
hydraulic
fluid
(13,
Consum-
2).
O-ring (17) and retainer rings in the upper bearing (16) of the cylinder assembly (9).
O-ring and retaine rs i nto pos ition. Refer to Figu re 5-1 0.
Two dowel rods
may be used to work
Soak the felt
b.
bearings (16
c.
se
and
pad (26)
19).
in SAE 10W30 oil and install in the
cylinder assembly (9)
between the up per and lower
Slide the scraper seal (27) over the piston (28) and insert the lower shock assembly (35) into the
mbly (9). Wo rk the scrape r seal (27) i nto the lowe r end of the cylinder assembly (9) until seated.
E17
I
cylinder
as-
5-39
BEECH BARON 55 AND 58 SHOP MAN UAL
I nstal I u ppe r torq ue knee (23) to the cylinder assembly (9) and lower torque knee (34) to the lower shock assembly (35) using torque knee pins (21 and 31), retaining pins and cotter pins. Install stop (22) to the upper torque
knee pin (21). Insert the center torque knee bushing (24) and connect the torque knees (23 and 34) using bolt, washers and nut (32).
d.
e.
Lubricate
f.
I nstall
and
n ut
bearings
bushings (1 2)
new
(1 0).
at grease
fittings
into brace
with g Tease
I nstall brace
(1 1
1 n stall fo rwa rd and aft columns
(8, Consu mable Materials Chart, Section 2).
(15)
(1
onto the
1
to the brace
(1 1)
and
cylinder assembly (9) with bo it, co nnecto r
cylinder assembly (9) using main landing
(14).
gear brace bolts
Raise and block lower shock assembly (35) 1/4 inch from the fully compressed position and fill cylinder assembly (9) with hydraulic fluid (13, Consumable Materials Chart, Section 2) until the top of piston (28) is covered (approximately 2 pints of hydraulic fluid).
g.
h.
Install
ring (8)
O-ring (4),
valve
core
(2)
suction to
pull
assembly (3) into orifice tube (6). Assemble the O-ring (7) and piston
cylinder assembly (9). Slowly extend lower shock assembly (35) allowing the
the cylinder assembly (9), then install retainer ring (5).
and valve
to orifice tube and install into
orifice tube down into
WARNING
IWARNING
As with all
forming
i.
Inflate the
(6)
tube
j.
operations involving equipment under high pressure, exercise
areas directly above and below the strut.
caution when per-
the leak test; avoid the
cylinder assembly (9) to approximately 100 psi using dry air
assembly (3) with soapsuds and check for air leaks.
or
nitrogen.
Coat the top of the orifice
and air valve
Release the air pressure; clean the
fresh water and
soapsuds
off the top of the orifice tube
(6)
and air valve
assembly (3)
with
wipe dry.
k.
Install air valve cap
I.
Install all
m.
Install main wheel and brake
(1)
to air valve
assembly.
hydraulic plumbing, safety
switch components and
assembly.
clamps.
Refer to Section 5, INSTALLING THE WHEEL AND BRAKE ASSEM-
BLY.
n.
I nstall main la nding gear to the
o.
Service the main
5-40
landing
airplane. Refer to
Section 5, MAIN LANDING GEAR INSTALLATION.
gear. Refer to Section 2, SHOCK STRUTS.
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
C HA RT 5-2
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-251,TC-344, TC-355 AND AFTER; TE-1 AND AFTER; TH-1 AND AFTER)
O.D
I.R
ITEM
WEAR TOLERANCES AND INSPECTION
PROCEDURES
NOTE
Listed below
are
the tolerances used to determine the extent of
we a r
outside-diameter
Lower Shock
Pisto n
landing gear components.
and
A I I i n s id e-d i amete r
i n the main
permissible wear limits are given fo r tho s e components.
(O.D.) dimensions are given in inches. Refer to Figure 5-9.
Where pe rti nent, the
1
Visually inspect piston (28), axle (37) and
brazed retaining bolt (36) for wear, damage and
corrosion. Any sign of scratches and worn
areas which can not be repaired is cause for
rejection. Conduct a magnetic-particle
inspection per MIL-STD-1949. Any sign of
cracking is cause for rejection.
Assembly (35)
(28)
C h ro m e Portion
1 .602
1 .8635
1.593
1.8600
Visually inspect for wear, damage and
corrosion. Replace if wear tolerances are
exceeded.
Axle
1.498
(37)
1.497
Visually inspect for wear, damage and
corrosion. Strip and cadmium plate axle as
necessary, per Fed QQ-P-416, Type II, Class 2,
o n sc ratch ed or wo rn areas.
Upper
and Lower
Knees
(23
and
Torq ue
34)
damage and
magnetic particle
MIL-STD-1949. Any sign of
Visually inspect for
wear,
corrosion. Conduct
a
inspection
per
cracks, scratches
or worn areas
which
can
not
repaired is cause for rejection. Remove all
bushings and inspect bores for corrosion.
Replace bushings as needed and cadmium
plate per FED QQ-P-416, Type II, Class 2.
be
To rq u e Knee Bores
(20
and
0.6255
0.6245
30)
Visu ally i ns pect for wear, damage and
corrosion. Replace if wear tolerances are
exceeded.
Bushings (18
and
29)
0.5015
0.4995
Visually inspect for wear, damage and
corrosion. If bushings exceed weartolerances,
replace with new bushings. Alignment ream
new bushings to specified wear tolerances. Drill
out lubricator holes through bushings and install
lubricators.
E17
5-41
BEECH BARON 55 AND 58 SHOP MAN UAL
CHART5-2
MAIN LAN DING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-251 TC-344,
TC-355 AND AFTER; TE-1 AN D A FTE R; TH-1 AN D
ITEM
I.D.
O.D
AFTER) (CO NTIN U E D)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Knee Pins
(21 and 31)
0.4990
0.4980
Visually inspect for wear, damage and
corrosion. Any sign of scratches or worn areas
which can not be repaired is cause for rejection.
If no visible wear is evident, conduct magnetic
particle inspection per MIL-STD-1949. Any sign
of cracks is cause for rejection. Replace if wear
tele rances
Torque
Knee Center
are
exceeded.
Hinge
Joint
Bore
(Upper) (25)
Inspect for wear, damage and corrosion.
Replace if wear tolerances are exceeded.
0.4420
0.4370
Bushing (24)
0.3150
0.4360
0.3120
0.4330
Visually inspect for wear, damage and
corrosion. Replace if wear tolerances are
exceeded.
Bore
(Lower) (33)
Visually inspect for wear, damage and
corrosion. Replace if wear tolerances are
0.3175
0.3125
exceeded.
Orifi ce Assem bly
(6)
1 .560
1.557
Visu ally i nspect for wear, damage and
corrosion. Any sign of scratches or worn
which
can
not be
repaired
is
cause
for
areas
rejection.
Check the orifice O.D. does not exceed
wear
tolerances. Check that orifice hole does not
exceed 0.1 92/0.187 inch. Cadmium
necessary exceptfor ring
per Fed QQ-P-416, Type
Cylinder Assembly (9)
5-42
plate
groove in orifice
I, Class 2.
as
head,
Visually inspect for wear, damage and
corrosion. Any sign of cracks, scratches or worn
a reas which can not be repaired is cause for
rejection. If no visible wear is evident, conduct
fluorescent or dye penetrant inspection per MILST D -6866. Co rro s i o n proof pe r M I L-C-5541
and touch up paint as required.
E17
BEECH BARON 55 AND 58 SHOP MANUAL
C HA RT 5-2
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-251 TC-344,
ITEM
TC-355 AN D A FTER; TE-1 AN D AFTER; TH-1 AN D A FTE R)
I.D.
O.D
(CONTI N U ED)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
I nte rnal Beari ngs
Upper (16)
1.8695
1.8650
Visually inspect for wear, damage and
corrosion. Replace bearing if wear tolerances
are exceeded. If replacement is required,
remove the bearing from the cylinder assembly
(9) and measure the O.D. Select from the O.D.
dimensions below to determine the correct
re p I ace me nt
bea ri n g:
2.3225/2.3215 inches
(P/N
35-81 5246-1 3, Standa rd
Bearing)
2.3345/2.3335 inch es
(P/N 35-815246-23, Oversize Bearing)
2.3425/2.341 5 i nc hes
(P/N 35-815246-25,
Oversize
Bearing)
If the O.D. dimension of the
bearing is greater
replace ment d i me ns io ns above,
replace the cylinder assembly (9). If additional
than the
i nfo rmatio n is req u i red, contact the Tech n ical
Support Department of Raytheon Aircraft
Company, P.O. Box 85, Wichita, KS 67201.
E17
5-43
BEECH BARON 55 AND 58 SHOP MAN UAL
CHART 5-2
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-251, TC-344,
ITEM
TC-355 AN D AFTER; TE-1 AN D A FT E R; TH -1 AN D
I.D.
O.D
AFTER) (CONTINUED)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Lower
(19)
Visually inspect for wear, damage and
corrosion. Replace bearing if wear tolerances
are exceeded. If replacement is required,
remove the bearing from the cylinder assembly
(9) and measure the O.D. Select from the O.D.
1.8695
1.8650
dimensions below to determine the correct
re p lace m e nt
bea ri n g:
2.0035/2.0010 inches
35-81 5246-9, Standard
Bearing)
2.01 85/2.01 70 inches
Oversize
(P/N 35-815246-27,
If the O.D. dimension of the
than the
Bearing)
bearing
is
greater
d i me ns io n s above,
place
replace the cylinder assembly (9). If additional
information is required, contact the Technical
Support Department of Raytheon Aircraft
Company, P.O. Box 85, Wichita, KS 67201.
me nt
re
replacement of bearing is required, coat bore
locquic primer (72, Consumable Materials
Chart, Section 2) and install new bearing using
an adhesive (71, Consumable Materials Chart,
Section 2).
If
with
U ppe r To rq u e Knee
0.501 0
Attach me nt H o I e
0.4995
Visually inspect for
corrosion. Replace
wear,
if
damage
wear
and
tolerances
are
exceeded.
Do not
Instruction Placards
for
Brace
remove
inspection
from
Visually i nspect
Assembly (1 1
cylinder assembly except
pu rposes
or
rep raceme nt.
for wear, da mage and
a fluorescent or dye
corrosion. Conduct
penetrant inspection per MIL-STD-6866. Any
sign of cracks, scratches or worn areas which
can not be repaired is cause for rejection.
Hinge Bushings
Outer
5-44
Hinge (12)
0.7192
Replace bearings
0.71 84
overhauled.
when main
landing
gear is
E17
BEECH BARON 55 AND 58 SHOP MANUAL
C HA RT 5-2
MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PR OCEDUR ES
(TC-251, TC-344,
TC-355 AND AFTER; TE-1 AND AFTER; TH-1 AN D
I.D.
ITEM
O.D
AFTER) (CONTIN UED)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Inner
Hinge (13)
when main
0.6240
Replace bearings
0.6230
overhauled.
0.4425
Visually inspect for
corrosion. Replace
landing
gear is
Brace Bo res
Fo rwa rd Bolt
(1 4)
Bo re
0.4370
wear, da m ag e
if
wear
an d
tolerances
are
exceeded.
Center Bolt
(1 O)
Bore
inspect fo r wear, da mage an d
Replace if wea r tele rances a re
0.2520
Visual ly
0.2495
corrosion.
exceeded.
Aft Bolt
(14)
Bore
0.4425
0.4370
Visually inspect for wear, damage and
corrosion. Replace if wear tolerances are
exceeded.
Forward and Aft Columns
(1 5)
Upper
and Lowe r Attach me nt
(1 4)
Fo rwa rd Bolt
Bores
0.4425
Visually inspect
0.4370
corrosion.
for wear,
Replace if
damage
wear
and
tolerances
are
exceeded.
Aft Bolt
(14)
Bores
0.4425
0.4370
Visually inspect for wear, damage and
corrosion. Replace if wear tolerances are
exceeded.
Safety
Switch
Components
continuity when switch
Replace wiring and components on
Ensure there is electrical
is activated.
condition.
El 7
5-45
BEECH BARON 55 AND 58 SHOP MAN UAL
NOSE GEAR SERVICING
Service the
nose
gear. Refer to Section 2, SHOCK STRUTS.
LUBRICATION
Lubricate the
nose
wheel
bearings
and grease
fittings.
Refer to Section 2, LUBRICATION CHART.
NOSE WHEEL REMO VA L
a.
Jack the
b.
Remove the nut and
c.
Remove the
nose
wheel.
nose
bushing
wheel
which retains the
assembly by sliding
nose
wheel
assembly
on
the axle.
it off the axle.
NOSE WHEEL INSPEC TION A ND CLEANING
WARNING
IWARNING)
Dry cleaning solutions are toxic and volatile. Use in a well ventilated area. A void contact with
skin
a.
or
Degrease
clothing.
Do not inhale the vapors.
all parts and
dry thoroughly.
A soft bristle brush may be
us ed
to re move hardened grease, dust and
dirt.
I
Do not
b.
Visually inspect bearing
wear, cage
c.
spin bearings with compressed air.
CAUTION
CAVTION
This will
1
cause
damage
cups and cones for nicks, scratches, water staining,
or distortion. Replace if damaged o r wo rn.
galling,
heat discoloration, roller
damage, and cracks
Inspect the wheel bearing grease for contamination and solidification
Inspect wheel halves for cracks, corrosion and other damage.
replaced. Small nicks, scratches, or pits can be blended out using
d.
at each
maintenance
badly corroded castings
(400 grit) sandpaper.
Cracked
fine
periodic
or
inspection.
should be
e.
Inspectthe snap rings and grease seals for deterioration and wear; replace if damaged o r d efo rm ed. Satu rate
felt seal with 1 0W30 oil (remove excess by pressing slightly). Also coat the sides and outer diameter with grease (8,
Consu mable Materials Chart, Section
f.
2) prior to assembly.
Inspect the wheel bolts for cracks,
corrosion
or
other
damager Replace any cracked bolts.
NOSE WHEEL INS TALLA TION
a.
Clean and
repack wheel bearings.
Refer to Section 5, NOSE WHEEL INSPECTION AND CLEANING. Replace
retaining rings and snap rings are in p lace befo re i n stall i n g
any d a mag ed grease seals and insure the grease seal
the wheel.
5-46
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
NOTE
A
ijushing is pe rma nently i n stat led o n th e i n boa rd end of the axle. No other hardware is req u i red
between the wheel and the inboard end of the axle.
b.
Install the wheel, outer spacer,
c.
To rq ue the axle nut
as
fol lows:
Check for burrs
or
rough
1.
Chart, Section
2.
are
While
2)
retaining
threads
to the axle threads and
rotating
the wheel,
tighten
on
nut and cotter
the axle and
pin.
retaining
nut.
Apply
grease
(8,
Consumable Materials
surface of the nut.
bearing
retaining
the axle
n ut
to 150
200 i nch -pou nds to insu re that the beari ngs
p rope rly seated.
Back off the axle
While
rotating
retaining
the wheel,
n ut
to ze ro to rq ue.
torque the axle retaining
nut to 30
inch-pounds
and check for
alignment
of the
locking
holes.
If not at
a
locking position,
continue
tightening
the axle nut to the first
and install the cotter
locking position
pin.
NOSE GEA R RE~IO VAL
When removi ng the
gear, take
nose
care
to retain the
original adjustment
at the rod end
fittings
to facilitate reas-
sembly.
a.
Jack the
b.
Disconnect the
c.
D iscon nect the stee ring
d.
Disconnect the
e.
Rem ove the nuts, washe rs,
airplane and partially
drag leg
at its
retract the
fitting
mec han is m
landing
gear to relieve the load
the
nose
gear brace
at t he
nos e
g ea r.
on
on
the retract rod
compression springs.
assembly.
landing light wiring.
bolts, and bushings which
connect the nose gear upper brace to the wheel well
structure.
f.
Lower the
nose
assembly
gear
from the
nose
wheel well.
NOSE GEAR INSTALLA TION
a.
Carefu ily pos ition the
b.
Align bolt holes and install bushings, bolts, washers,
cotter pins.
new
nose
gear
assembly against
the
nose
wheel
and nuts.
we II
st ructu re.
Torque the
nuts to 1 50
200
inch-pou nds.
Install
NOTE
Use 100951S016YP washers
between the
nose
c.
Con nect the landi ng
d.
Connect the
El 7
drag leg
gear
light
(maximum
assembly
of two per
side)
to obtain total end
play
of 0 to 0.015 inch
and supports.
wi re.
of the
nose
gear brace
assembly.
5-47
BEECH BARON 55 AND 58 SHOP MAN UAL
e.
Con nect th e stee ri ng
mec ha n is m
to th e
nose
gear.
CAUTION 1
I CAVTlOhl
Excessive
landing
f.
operation
of the
gear motor. Allow
Operate the landing gear and
complete cycles.)
a
landing gear motor without proper cooling may ca use da mage
short cooling time after each extension and retraction cycle.
check for proper
rigging
and
nose
adjustment. (Cycle
gear
the
to the
landing
gear
a
min-
imum of six
NOSE GEA R-O VERHA UL
(TC- 1
A ND A FTER; TE- I THRU
TE-300)
NOTE
Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in Section 15 for time limits and maintenance checks of the
nose
Experience in the field indicates
assembly. The forces
the barrel
gear.
the
points
exerted
of greatest wear on the nose gear are the upper and lower bearings in
the bearings during takeoff and landing tend to result in an oversized
on
condition. The oversized condition of the upper
the upper bearing and O-ring. This will
through
bearing in the barrel assembly will result in leakage of hydraulic fluid
eventually cause flu id to seep down th rough the felt pad and out the
lower beari ng.
replacement of the scraper ring and all O-rings in the landing gear fails to stop leaks, the oversized condition
bearings is probable. In such instances the landing gear should be overhauled. The following information will
aid in dete rm i n i n g th e exte nt of lan d i n g gear wear and whether it is possible to overhaul or necessary to replace
critical landing gear components.
When
of the
NOSE G EAR DISASSEM B LY
I
(TC-I
AND
AFTER; TE-1 TH RU TE-300)
FIGURE 5-11
WARNING
IWARNINO)
begin
Do not
disassembly
any
of the
nose
landing
gear until all air pressure has been
re-
leased.
a.
(1)
Place the strut in
is
vertical
a near
position
the valve
prevent the hydraulic fluid from spilling when the air valve assembly
to deflate the strut and
b.
Depress
c.
Rem ove the
d.
Remove the snap
ring (4) retaining
e.
Retract the
and fork
f.
Remove the orifice tube
g.
Invert the
5-48
to
re moved.
nose
piston
nose
core
remove
the air valve
assembly (1).
wheel. Refer to Section 5, NOSE WHEEL REMOVAL.
the orifice tube
assembly (48)
(6).
Remove the
gear and d rai n out the
to
push
(6).
the orifice tube
O-ring (5)
and
(6)
out of the barrel
(23).
piston ring (7).
hyd rau lic fl u id.
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
WARNING
1WARN1NO)
Do not disconnect the torque knees (37 and 46) without first deflating the nose gear. The
torque knees provide the extension stop for the piston and fork assembly (48). When disconnected, the piston and fork assembly (48) is free to slide out of the barrel (23).
h.
Remove the cotter
pin (40),
nut
i.
Remove the cotter
pin (36),
and
j.
Remove the cotter
pin (50), pins (42
k.
Slide the
i.
Remove the lower snap
piston
and fork
(41), washers (39
pins (25
and
assembly (48)
ring (33),
and
47),
34)
and
44), bushing (45),
to disconnect the upper
and washers
out of the barrel
scraper
(31),
and bolt
and
(49 and 51)
(23).
torque knee (37).
to disconnect the lower
Remove the collar
n.
Remove the
Remove the nut
brace
o.
E17
and
and shim
(3).
19), bushing (18),
and bolt
(21) attaching
Removal of the
O-ring
may be
1
the
shimmy damper (20)
to the
(15).
Remove the nut
from the barrel
p.
(16), washers (17
(2)
torque knee (46).
adapter (32).
O-ring (38) and remove the felt pad (24) from inside the barrel (23).
simplified by using a hook manufactured from music wire. Refer to Figure 5-10.
m.
(43).
(30),
washers
(27
and
29), bushing (28),
and bolt
(26)
to disconnect the
shimmy damper (20)
(23).
Pull the barrel
(23)
out of the brace
(15).
5-49
BEECH BARON 55 AN D 58 SHOP MAN UAL
/nl
VALVE
COLLAR
I
AIR
2.
3.
S
4.
5.
~i"
‘J /h~3:
2
6.
i.
8.
9.
IO.
4
12.
13.
5
23
14.
15.
16.
6
24,
L
I
17.
i
I
25
26
1
18´•
19.
~O
21.
22.
23.
24
25.
ASSEMBLY
26
BOLT
27.
SHIM
SNAP RING
O-RING
ORIFICE TUBE
PISTON RING
UPPER BEARING
COTTER PIN
28.
29.
30.
31.
WASHERS
BUSHING
WASHER
NUT
SCRAPER
32
ADAPTER
33.
34
LOWER
PIN
NUT
WASHER
BUSHING
WASHER
(AS REQUIRED)+
BOLT
BRACE
NUT
WAS HER
35.
36.
37.
38.
39.
40.
41.
42.
43.
BUSHING
44.
8USHINGS
COTTER PIN
UPPER TORQUE KNEE
O-RING
WASHERS
COTTER PIN
NUT
PIN
BOLT
WASHER
BUSHING
IOWER TORQUE KNEE
PIN
PISTON AND
FORK ASSEMBLY
WASHtK
SH I MMY
BOLT
45.
DA MPER
46.
47.
48.
LOWER BEARING
BARREL
FELT PAD
PIN
49.
50.
27
51.
52.
7
SNAP
WASHER
COTTER
WASHER
AXLE
RING
PIN
29
30
36
37-
3 1
38
32
F-42
9
33
40
10
i
41
LII
12
15
43
dd
d7
45
yl
j
16
46
4950
i
o
W=
17
18
51
52
O
x
-r+
USE 1 0095 1 SO i 6 YP WASHERS AS RE QU I R ED PER
SIDE TO OBTAIN MAXIMUM TOTAL END CIEARANCE
OF .015 INCH.
PEEL LAMINATIONS AS NECESSARY FOR FREE
OPERATION. MAXIMUM CLEARANCE IS .012 INCH.
Nose Gear
5-50
22
Assembly (TC-1 and after;
Figure 5-11
I~----;rli
TE-1 thru
C94EA32B2228
TE-300)
E17
BEECH BARON 55 AND 58 SHOP MANUAL
NOSE GEAR
CLEANING, REPLACEMENT
PARTS AND R E PAIRS
(TC-1
AN D A FTER; TE-1 TH RU
TE-300)
CLEANING (TC-1 AND AFTER; TE- 1 THRU TE-300)
a.
Clean all parts with solvent
dry
after
b.
I mme rse all internal pa rts in clean
(15, Consumable
Materials Chart, Section
2). Remove all
excess
solvent and
wipe
cleaning.
REPLACEMENT PARTS
(TC-1
hyd rau lic flu id (1 3,
Cons u mable Mate rials C hart, Section
AND AFTER; TE-I THRU
2) p rio r to
asse
mbly.
TE-300)
FIG URE 5- 1 I
a.
I
Inspect all parts and assemblies for damage or excessive wear.
Wear which is greater than the allowable
Damage
which cannot be corrected
Screws that
Parts that
are
are
severely damaged
cracked, chipped
Parts that have corrosion
b.
or
or
(32)
Bu sh i ng
(1 2)
or
following
conditions
are cause
for
rejection:
tolerances. Refer to Chart 5-3.
repaired.
have
stripped, severely
worn or sco red
th reads.
broken.
other defects that cannot be
R e p lace t he fo I lowi n g pa rts whe n
Ad apte r
or
wear
The
nose
gea r is
repaired.
ove rh a u le d:
Cotter Pins
Pelt Pad
Piston
(24)
Ring (7)
O-Rings (5, 38)
Safety
Wire
Sc rape r
(31
Snap Rings (4, 33)
c.
Replace
the
following parts
on
condition when
nose
gearis
overhauled:
Bearings (8, 22)
Bush in gs
Grease
(1 8, 28, 35, 45)
Fittings
Placards
Valve Co re
El 7
(1
5-51
BE ECH BARON 55 AND 58 SHOP MANUAL
REPAIRS
I
AND AFTER; TE- I THRU
(TC- 1
TE-300)
FIGURE 5-II
a.
Visually inspect castings for cracks
and
wear.
cess ive
ly
wo rn
pitting;
and finished surfaces for
determining
scoring, pitting, nicks, cracks, distortion
wear. Replace all defective and ex-
the extent of
parts.
If fluid leaks have been observed
b.
and
Refer to Chart 5-3 for tolerances to aid in
on
top of the air valve assembly (1), check the small O-ring of the valve; then
look for defects in the valve.
If the leak is from the
c.
junction of
the orifice tube
(6)
and the barrel
(23),
check the O-ring
(5)
on
the orifice tube
(6).
d.
All parts
or
repaired
assemblies may be
Slight scoring
of shafts may be
if any of the
co rrected
following problems
by lapping
caref ully with
a
exist:
flat oil stone.
NOTE
Do not exceed 10% of the
component material thickness when removing nicks, burrs and scratch-
es.
Smooth minor nicks, burrs, and scratches.
Those
as
parts that
that removed
or
Minor thread
scratched
are
be
replaced
or
with
damage, chase
have
new
worn
plating
may’be stripped and replated with the
same
type of plating
parts.
to clean or smooth.
NOTE
inspection to determine the depth of penetration and the cross-sectiondamaged area must be tho ro u g h ly cleaned and the corrosion must be removed. The deterioration caused by corrosion or removal of corrosion must not reduce the material
thickness of any component by mo re th a n 1 O%. Refe r to Chart 5-3 fo r NOSE G EAR WEAR TOLCorrosion damage requires
al
area
change.
The
ERANCES AN D I N SP ECTIO N PROCEDURES
the Technical
Support Department of Raytheon
Remove corrosion if
mium
plate
on
components. For additional information contact
Company, P.O. Box 85, Wichita, KS 67201.
Aircraft
applicable, and apply corrosion prevention
Type II.
materials
as
necessary per MIL-C-5541
or
cad-
per Fed QQ-P-416,
Bushings
that check within allowable
When evidence of
damage
wear
tolerances may be reused.
exists to steel parts,
magnetic particle inspect
per MIL-STD-1949.
NOTE
dye penetrant inspected per MILSTD-6866. If the finish absorbs the penetrant so that bleed out prevents satisfactory inspection or
if a new finish has not cured for at least 30 days, contact the Technical Support Department of Raytheon Aircraft Company, P.O. Box 85, Wichita, KS 67201.
Do not
I
remove
When evidence of
6866, Type
5-52
paint
or
damage
primer from
the
area to
be fluorescent
or
exists to metal parts other than steel, fluorescent
penetrant inspect per MIL-STD-
i.
El 7
BEECH BARON 55 AND 58 SHOP MAN UAL
Replace damaged
or
unserviceable parts with
NOSE GEAR ASSEMBLY
new or
serviceable parts.
AND AFTER; TE-1 THRU
(TC-1
TE-300)
1
FIGURE 5-11
NOTE
Prior to
assembly,
immerse all internal
Mate rials Chart, Section
O-ring (38) into
position. Refer to Figure 5-10.
a.
Install
new
pad (24)
b.
Saturate felt
c.
Install
d.
Install barrel
(23)
e.
Install shims
(3)
new
scraper
the upper
bearing
(23).
of the barrel
Two dowel rods may be used to work
O-ring
into
1
with SAE 10W30 oil before installation. Install felt
(31), adapter (32)
into the brace
as
parts (except felt pad (24) in hydraulic fluid (13, Consumable
2).
and
secure
with lower snap
(23).
in the barrel
pad (24)
ring (33).
(15).
necessary.
NOTE
Add
or remove
(3)
(15).
lamination from shims
0.012 between collar
(2)
and brace
fo r f ree
as necessa ry
o pe rati on.
M axi m u m
c I ea ra nce
is
(2) to brace (15) and tighten two bolts securing collar. Rotate collar to ensure freedom of movement
after tighting bolts. Adjust shims (3) as necessary to allow collar to rotate freely. Secure bolts with safety wire.
f.
Install collar
g.
Install air valve
h.
I nstal I
u ppe r
valve
assembly (1) excluding
to rq u e knee
(37)
with the
core.
pins (25 and 34), and
pin (36).
cotter
NOTE
Install the washers
my
damper (20)
(17
19) above or below the bushing (18)
lug on the barrel (23).
and
with the
shimmy damper (20)
and install the
i.
Position
j.
Install the
k.
S I i d e th e p i sto n and fork
I.
Connect the lower torque knee
bushing (28),
bolt
Install the bushing (45), bolt
lowertorque knees (37 and 46)
o.
(46)
(43),
(27
and
29)
and nut
into the barrel
with the
washers
pins (42
(39
and
new
Lubricate
bearings
at grease
fittings
with grease
(21),
(30)
(15)
the brace
washers
(17
and
to connect the
to
align
the shim-
19) and
nut
(16).
shimmy damper (20).
(23).
and
44),
47),
nut
O-ring (5) and piston ring (7) to orifice tube (6).
by attaching snap ring (4) to the top of collar (2).
Install
secure
washer
assembly (48)
m.
n.
(26),
bolt
bushing (18),
on
washers
(41)
(49
and cotter
and
51)
pin (40),
Push orifice tube
(6)
and cotter
pin (50).
to connect the upper and
down into the barrel
(8, Consu mable Materials Chart,
Section
(23)
and
2).
position and approximately 1/4 inch from fully compressed, fill through the air valve
assembly (I)with approximately 500/550 cc of hydraulic fluid (13, Consumable Materials Chart, Section 2).
p.
El 7
With the strut in the vertical
5-53
BEECH BARON 55 AND 58 SHOP MAN UAL
q. Fully extend and recompress the piston and fork assembly (48) three times or until
add ed. Add add itio nal flu id as required with the strut in the compressed position.
r.
With the
piston
and fork
assembly (48) compressed,
install the valve
core
no
additional fluid
into air valve
can
be
assembly (1).
WARNING
IWARhllhlG)
As with all
forming
s.
To leak test, inflate the
and air valve
t.
operations involving equipment under high pressure, exercise
areas directly above and below the strut.
caution when per-
the leak test; avoid the
assembly (1)
nose
with
gear to
approximately
soapsuds
90
psi using dry
air
or
nitrogen.
Coat the
top of the collar (2)
and test for air leaks.
Release the air pressure by depressing the valve core in the air valve
(2) and air valve assembly (1) with fresh water.
assembly (1).
Clean the
soapsuds from
the top of the collar
u.
Install the air valve cap
v.
Install the
w.
Install
x.
Service the
5-54
nose
nose
on
the air valve
wheel onto the axle
gear onto the
nose
airplane.
assembly (1).
(52).
Refer to Section 5, NOSE WHEEL IN STALLATION.
Refer to Section 5, NOSE GEAR INSTALLATION.
gear. Referto Section 2, SHOCK STR UTS.
El 7
BEECH BARON 55 AND 58 SHOP MAN UAL
C HA RT 5-3
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDUR ES
(TC-1
ITEM
I.D.
AND AFTER; TE-1 THRU
O.D.
TE-300)
WEAR TOLERANCES AND INSPECTION PROCEDU RES
NOTE
Listed below
are
the tolerances used to determine the extent of
wear
diameter
Collar
(2)
Torq ue
(37
and
nose gear components. Whe re
and outsideAl I i nside-diamete r
i n the
permissible wear limits are given for those components.
(O.D.) dimensions are given in inches. Refer to Figure 5-11.
pe rti ne nt, the
1
and corrosion.
Any
repaired is cause for
rejection. Conduct magnetic particle inspection per MIL-STD1949. Any crack is cause for rejection. Replace if wear
tolerances are exceeded, cadmium plate as necessary per
Fed. QQ-P-416, Type II Class 2.
0.3150
Visually inspect
0.3120
scratches
for wear, damage
which can not be
or worn areas
Knee As sem b ly
Visually inspect
46)
scratches
for wear, damage and corrosion. Any
which can not be repaired is cause for
or worn areas
bushing and inspect bores for corrosion.
proof as necessary per MIL-C-5541. Any crack is
for rejection. Replace bushing as needed.
rejection.
Remove all
Corrosion
cause
UpperTorque
Knee
(37)
Bore
Bushing (35)
for wear, damage and corrosion.
are exceeded.
0.4380
Visually inspect
0.4370
wear
0.3775
Visually inspect
0.3745
exceed 0.3775 inches I.D.,
tolerances
Replace
if
damage and corrosion. If bushings
replace with new bushings.
Alignment ream new bushings to specified wear tolerances.
Drill out lubricator holes through bushings and install
for wear,
lubricators.
Knee Pin
(34)
0.3735
Visually inspect
0.3725
scratches
for wear, damage and corrosion. Any
which can not be repaired is cause for
or worn areas
rejection. If no visible wear is evident, conduct a magnetic
pa rticl e i nspecti on per MIL-SID-1 949. Any crack is cause for
rejection. Replace if wear tolerances are exceeded.
Torque Knee Center Hinge
Joint
Bo re
(Uppe r)
Bushing (45)
Bore
E17
(Lowe r)
and corrosion.
Replace
if
for wear, damage and corrosion.
tolerances are exceeded.
Replace
if
for wear, damage and corrosion.
are exceeded.
Replace
if
0.31 50
Visually inspect for wear, damage
0.3120
wear
tolerances
0.2505
0.311
Visually inspect
0.2495
0.310
wear
0.31 50
Visually inspect
0.3120
wear
tolerances
are
exceeded.
5-55
BEECH BARON 55 AND 58 SHOP MAN UAL
CHA RT 5-3
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-1
ITEM
Lower
AN D
I.D.
AFTER; TE-1 TH RU TE-300) (CONTINUED)
O.D.
WEAR TOLERANCES AND INSPECTION PROCEDURES
Torque Knee (46)
Bore
Knee Pin
0.3775
Visually i nspect
0.3745
wear
(42)
tolerances
fo r wear, damage and corrosio n. Re place if
are exceeded.
for wear, damage and corrosion. Any
which can not be repaired is cause for
0.374
Visually inspect
0.373
scratches
or worn areas
rejection.
If
no
visible
wear
is evident, conduct
a
magnetic
pa rt ic le i ns pecti on per M IL-STD-1 949. Any crack is cause for
rejection. Replace if wear tolerances are exceeded.
Orifice
Assembly (6)
P/N 35-825195
(TC-1 th ru TC-2433,
th ru TE-300)
for wear, damage and corrosion. Any sign of
worn areas which can not be repaired is cause for
1.449
Visually inspect
1.436
scratches
or
rej ection. Cond u ct a
STD-1949. Any sign
TE-I
mag netic- partic le i n s pectio n per MILof cracking is cause for rejection. Check
the orifice O.D. does not exceed
wear
tolerances. Check that
orifice hole does not exceed 0.185/0.180 inches. cadmium
plate
as
necessary per Fed QO-P-416,
NOTE: If the orifice
tolerances,
use
Type I,
Class 2.
assembly P/N 35-825195 exceeds
Assembly P/N 36-820021 as a
wear
Orifice
re p laceme nt s pa re.
Orifice
Assembly (6)
P/N 36-820021
(TC-2434
an d
afte r)
for wear, damage and corrosion. Any sign of
orworn areas which can not be repaired is cause for
1.449
Visually inspect
1.436
scratches
magnetic-particle inspection per MILAny sign of cracking is cause for rejection. Check
rej ect i o n. Co nd u ct
STD-1949.
a
the orifice O.D. does not exceed
wear
tolerances. Check that
orifice hole does not exceed 0.1 42/0.1 40 inches. cad miu m
plate
Ba rre I Assem b ly
as
necessary per Fed QQ-P-416,
Visually inspect
(23)
scratches
Type I,
Class 2.
for wear, damage and corrosion. Any sign of
which can not be repaired is cause for
or worn areas
rej ection. Cond uct
STD-1949.
a
Any sign
magnetic-particle inspection per MILof cracking is cause for rejection.
Bearings
Upper
1 .755
1.751
Lower
1.755
1.751
U p pe r Torq ue Knee
Attach m e nt Hol e
5-56
Visually inspect for wear, damage and
barrel assembly if wear tolerances are
corrosion.
Repf ace
exceeded.
Visually inspect for wear, damage and corrosion. Replace
barrel assembly if wear tolerances are exceeded.
0.3755
Visually inspect
0.3745
wear
tolerances
for wear, damage and corrosion.
a re exceed ed.
Replace if
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
CHA RT 5-3
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TC-1
ITEM
AN D AFTE R; TE-1 TH RU
I.D.
O.D.
TE-300) (CONTINUED)
WEAR TOLERANCES AND INSPECTION PROCEDURES
Piston and Fork
Assembly (48)
Ch ro me Portion
(top)
Visually inspect
1.490
if
Axle
(52)
1.249
1.248
Brace
Assembly (15)
for wear,
Any sign of
repaired is cause
for rejection. Conduct a magnetic-particle inspection per MILSTD-1949. Any sign of cracking is cause for rejection. Replace
scratches and
1.482
wear
damage
worn areas
tolerances
are
Visually inspect for
which
and corrosion.
can
not be
exceeded.
wear,
damage
and corrosion.
Any sign of
repaired is cause
for rejection. Conduct a magnetic-particle inspection per MILSTD-1949: Any sign of cracking is cause for rejection. Strip
and cadmium plate axle as necessary, per Fed QQ-P-416,
Type II, Class 2 on scratched or worn areas.
scratches and
worn areas
Visually inspect
which
can
not be
for wear, damage and corrosion. Any
which can not be repaired is cause for
scratches
or worn areas
rejection.
Remove all
bearings and inspect for corrosion.
dye penetrant ins pection per M I L- STD6866. Any crack is cause for rejection. Coat interior of brace
and hinge bearing holes with corrosion preventative compound
per MIL-C-16173, Grade 1 or 2. Replace all bearings when
Cond uct flue rescent
nose
Hinge Bushings (1 2)
gea r i s
0.4692
Replace
0.4682
ream new
or
ove rhau led.
bea ri ngs wh en
lubricator
nose gear is overhauled. Alignment
bearings to specified wear tolerances. Drill out
holes through bearings and install lubricators.
I nte mal Beari ngs
Upper and
(8 and 22)
Lower
2.252
Replace
2.250
ream new
bea ri n gs wh en
lubricator
Instruction Placards
Do not
remove
purposes
El 7
nose gear is overhauled. Alignment
bearings to specified wear tolerances. Drill out
holes th rough bearings and install lubricators.
or
from brace
assembly except
for
inspection
replacement.
5-57
BEECH BARON 55 AND 58 SHOP MAN UAL
NOSE GEA R-O VERHA UL
A ND A FTER; TH- I A ND A FTER)
(TE-30 1
NOTE
Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in Section 15 for time limits and maintenance checks of the nose gear.
Experience
in the field indicates the
in the strut
housing.
points
The forces exerted
of greatest wear on the nose gear
the bearings during takeoff and
on
condition. The oversized condition of the upper and lower strut
bearings
will
the upper and lower strut bearings
landing tend to res u it i n an oversized
eventually result in leakage of hydraulic
are
fluid.
When
replacement of all O-rings in the landing gear fails to stop leaks, the oversized condition of the bearings is
probable. In such instances the landing gear should be overhauled. The following information will aid in determining
the exte nt of land i ng gear wear and wh ethe r it is possible to overhaul or necessary to replace critical landing gear
components.
NOS E G EAR DISASS EM B LY
I
(TE-301
AN D AFTE R; TH-1 AN D A FT ER)
FIGURE 5-12
a.
Place the
sembly (14)
gear in
nose
a near
vertical
position
prevent the hydraulic fluid from spilling when the air valve
to
as-
is removed.
WARNING
IWARNINO)
Do not
remove
the air valve
b.
Release the air pressure in the
c.
I nve rt th e
d.
Cut the
safety
nose
wire and
Remove the upper strut
remove
housing
housing (15)
hyd rau lic
the bolts
retainer
cause
gear, cut the
gear and drain out the
n o se
(2),
Slide the strut
f.
Remove the nut, washers, bolt
(19)
and
personal injury
safety
wire and
or
property damage.
remove
the air valve
assembly (14).
fl u id.
the upper strut housing retainer
laminated shims (3) and spacer (4).
attaching
out of the gear brace
e.
until all air pressure has been released. It may be
assembly (14)
blown out with considerable force and
(2)
to the gear brace
(6).
(6).
bushing (20) connecting
the upper and lower torque knees
(18
and
22)
together.
NOTE
Only
remove
bushings (21 and 25)
safety wire
g.
Cut the
h.
Slide the
i.
Remove items
j.
Rem ove the nut, washers, seal
k.
Rem ove the nut and washer
5-58
piston
and
remove
and axle
when
required
the lower strut retainer
assembly (40)
(30) through (38)
(29),
piston
O-ring (28)
strut
housing (15), using
a
spanner wrench.
housing (15).
and axle
and the orifice rod
and the
replacement.
(39) from the
out of the strut
from the
(13),
for
assembly (40).
assembly (26).
and orifice
(27)
from the orifice rod
assembly (26).
El 7
BEECH BARON 55 AND 58 SHOP MAN UAL
WARNING
IWARNINO)
Do not disconnect the
torque knees (18 and 22) without first deflating the nose gear. The
torque knees provide the extension stop for the piston and axle assem bly (40). When disconnected, the piston and axle assembly (40) is free to slide out of the strut housing.
NOTE
Only
i.
Remove the roll
remove
bushings (16)
pin (17), retaining pin,
when req uired fo r
washers and cotter
replacement.
pin attaching
the upper torque knee
(18)
to the strut
housing (15).
NOTE
O n ly
m.
axle
n.
rem ove
bushings (24)
Remove roll
asse
pin (23), retaining pin, washers and
mbly (40).
Remove
steering straightener bearing (1) from
when req u i red for
cotter
replaceme nt.
pin attaching the
the upper strut
lower torque knee
(22) to the piston
and
housing retainer (2).
NOTE
The small alien head
not be
N OS E G EA R
CLEANING
a.
re moved
screw
unless
at the
top of the
replaceme nt
strut
housing (15) is a bonded
(1 2) is necessary.
installation and should
of the fill tu be
CLEANING, REPLACEMENT PARTS AND REPAIRS (TE-301 A N D A FTE R; TH -1 AN D AFTER)
(TE-301
AND AFTER; TH- 1 AND
Clean all parts with solvent
(15,
AFTER)
Consumable Materials Chart, Section
2).
Rinse and
dry thoroughly after clean-
ing.
b.
El 7
Immerse all internal parts in clean
hydraulic fluid (1 3, Consumable
Materials Chart, Section
2) prior to assembly.
5-59
BEECH BARON 55 AND 58 SHOP MANUAL
4
STRAIGHTENER BEARING
UPPER STRUT HOUSING RETAINER
LAMINATED SHIMS
SPACER
UPPER GEAR BRACE BEARING
GEAR BRACE
HINGE BUSHINGS
BUSHINGS
BUSHINGS
LOWER GEAR BRACE BEARING
SPACER
FILL TUBE
WASHERS, SEAL, AND NUT
AIR VALVE ASSEMBLY
STRUT HOUSING
TORQUE KNEE BUSHINGS
UPPER TORQUE KNEE ROLL PIN
UPPER TORQUE KNEE
BOLT, WASHERS, NUT
TORQUE KNEE BUSHING
TORQUE KNEE BUSHING
LOWER TORQUE KNEE
LOWER TORQUE KNEE ROLL PIN
TORQUE KNEE BUSHINGS
TORQUE KNEE BUSHING
ORIFICE ROD ASSEMBLY
I
1
I
2.
5
_7
3.
4.
5.
6.
7
8.
9.
IO.
I I
k~e
6,
12.
13.
14.
~s.
15.
16.
17.
18.
19.
lo~
c~
20.
B
21.
22.
23.
24.
I I-
25
26.
15
1 7
--~a
19
30
18
37
38
2J
24
S
~39
‘Q~
21
22
d
~5
27
~8.
29.
30,
31.
32.
33.
34.
35.
36.
37.
38.
39.
40.
41.
42.
ORFICE
O-RING
WASHER AND NUT
RETAINER RING
UPPER STRUT BEARING
RETAINER RING
REBOUND TUBE
O-RING
LOWER STRUT BEARING
BACKUP RINGS (2)
O-RING
BACKUP RINGS (2)
LOWER STRUT RETAINER
PISTON AND AXLE ASSEMBLY
AXLE
AXLE BEARING
26
40
27-
R3
28
29
33
34
35
36
41
O
42
C94TC0582969
Nose Gear
5-60
Assembly (TE-301 and after;
Figure 5-12
TH-1 and
C
after)
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
REPLACEMENT PARTS
(TE-301
AND AFTER; TH-1 AND
AFTER)
NG URE 5- 1 2
Inspect all parts and
a.
assemblies for damage
Wear which is greater than the allowable
Damage
which cannot be corrected
Screws that
Parts that
are
are
severely damaged
cracked, chipped
Parts that have corrosion
b.
or
or
or
or
or
wear
excessive
The
following conditions are cause for rejection:
tolerances. Refer to Chart 5-4.
repaired.
have
stripped, severely
worn or
scored threads.
broken.
other defects that cannot be
R ep lace t h e fo I lowi ng pa rts whe n
wear.
nose
gea r is
repaired.
ove rh a u led.
Backup Ring (36, 38)
Bushings (7, 8, 9, 16, 20, 21,24, 25)
Cotter Pins
Lower Strut Retainer
(39)
O-Rings (28, 34, 37)
Safety
c.
Wire
Replace
the followin g parts
on
condition when
nose
gear is
ove rhau led:
Bearings (5, 10, 31, 35)
Grease
Fittings
Placards
Spacers (4, 11)
Valve Core
REPAIRS
(TE-301
AND AFTER; TH- 1 AND
AFTER)
FIG URE 5- 12
a.
Visually i nspect casti ngs for c racks
and
wear.
cessively
b.
and
pitting;
and fi ni shed
Refer to Chart 5-4 for tolerances to aid in
worn
su rf aces
determining
fo r sco ri ng, p itti ng,
the extent of
wear.
n
icks, cracks, d isto rtion
Replace
all defective and
ex-
parts.
If fluid leaks have been observed
on
top of the air valve assembly (14), check the small O-ring of the valve; then
look for defects in the valve.
c.
All parts
S I i g ht
E17
or
assemblies may be
sco ri n g
repaired if any of
of shafts may be corrected
the
following
by lapping carefully
p rob re ms
with
a
ex ist.
flat oil stone.
5-61
BEECH BARON 55 AND 58 SHOP MAN UAL
NOTE
Do not exceed 10% of the component material thickness when
removing nicks,
burrs and scratch-
es.
Smooth minor nicks, burrs, and scratches.
Those
as
parts that
that removed
Minor thread
or
are
be
scratched
replaced
damage,
or
with
have
new
chase to clean
worn
plating
may be
stripped
and
replated
with the
same
type of plating
parts.
or
smooth.
NOTE
damage requires inspection to determine the depth of penetration and the cross-sectional area change. The damaged area must be thoroughly cleaned and the corrosion must be removed. The deterioration caused by corrosion or removal of corrosion must not reduce the material
thickness of any component by more than 10%. Refer to Chart 5-4 for NOSE GEAR WEAR TOLCorrosion
components. For additional information contact
the Technical Support Department of Raytheon Aircraft Company, P.O. Box 85, Wichita, KS 67201.
E RAN C ES AN D I NSP ECT I ON PROCEDURES
I
Remove corrosion if
mium
plate per
Fed
applicable,
and
prevention
materials
as
necessary per MIL-C-5541
or
cad-
QQ-P-416, Type II.
that check within allowable
Bushings
corrosion
apply
on
When evidence of
damage
wear
exists to steel
tolerances may be
re u sed.
parts, magnetic particle inspect per MIL-STD-1949.
NOTE
Do not re move paint or primer from the area to be fluorescent or dye penetrant inspected per MILSTD-6866. If the finish absorbs the penetrant so that bleed out prevents satisfactory inspection or
if a new finish has not cured for at least 30 days, contact the Technical Support Department of Ray-
I
theon Aircraft
Company,
When evidence of
P.O. Box 85, Wichita, KS 67201.
damage exists
to metal
parts other than steel, fluorescent penetrant inspect per MIL-STD-
6866, Type I.
Re p lace da mag ed
or
unserviceable parts with
NOSE G EAR ASS E M B LY
I
(TE-301
AND
new or
serviceable parts.
AFTER; TH-1 AN D A FTE R)
F’ GU RE 5-12
a.
In stall the
steering straightener bearing (1)
on
the upper strut
housing retainer (2).
NOTE
New
b.
bushings (24)
are
to be installed if
Attach the lower torque knee
and cotter
5-62
(22)
to the
they
piston
have been removed
and axle
during
assembly (40)
the
with roll
nose
gear
disassembly.
pin (23), retaining pin,
washers
pin.
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
NOTE
New
c.
bushings (16)
are
to be installed if
Attach the upper torque knee
(18)
they
to the strut
have been removed
housing (15)
with roll
during
the
nose
gear
disassembly.
pin (17), retaining pin,
washers and cotter
pin.
d.
Lubricate the bore of the strut
ameter of the
Consumable
housing (15), orifice rod assembly (26), orifice (27) and O-ring (28), the outer dipiston (40), O-ring (34) and items (30) through (39) with a light coating of clean hyd rau lic fl u id (1 3,
Materials Chart, Section 2).
e.
Install the
f.
Install the orifice rod
and orifice
O-ring (28)
(27)
assembly (26)
on
the orifice rod
assembly (26)
in the bore of the strut
with washer and nut
housing (15)
with the
(29).
washers, seal and
nut
(13).
I nstall O-ri ng (34) i nside th e strut hous i ng (1 5). Assemble items (30) th rou g h (39) on th e pisto n end of the p iston
g.
and axle assembly (40). Slide the piston and axle assembly (40) into the strut housing (15). Tighten the lower strut
retainer
(39) using
a
spanner
wrench, and safety wire.
NOTE
New bushings (21
assembly.
h.
and
25)
are
to be installed if
Connect the upper and lower torque knees
(18
they
and
22)
have been removed
during
with bolt, washers, nut
Slide the strut housing (15) into the gear brace (6). Insure that the spacer
i.
down between the gear brace and the strut housing.
(11)
(19)
the
and
nose
gear dis-
bushing (20).
is installed with the coated side
NOTE
Add
lamination from shims
or remove
0.010 inch between the strut
(3)
housing (15)
as necessa ry
fo r f ree
and the gear brace
o pe rati on.
Place the gear brace (6) in the vertical position. Assemble the laminated shims
strut housing retainer (2). Insure that the coated side of the spacer (4) is facing up.
housing
the strut
over the top of the strut
(2)
housing (15).
k.
Install the bolts
I.
With the
valve
attaching
housing (15)
the upper strut
housing
and
measure
retainer
(2)
and
c I ea rance
is
(6).
j.
retainer
M ax i m u m
(3) and spacer 14)
Loosely install the
in the upper
upper strut
the distance between the gear brace (6) and
safety
wire.
gear in a vertical position and the piston and axle assembly (40) compressed, fill through the air
hole with approximately 1 pint of hydraulic fluid (13, Consumable Materials Chart, Section 2). When
nose
assembly
the fluid overflows,
cycle
the
piston and axle assembly (40) (full extension to compressed) and refill. Repeat until
housing (15) with the piston and axle assembly (40) in the compressed position.
fluid cannot be added to the strut
m.
Install the air valve
n.
To leak test
and upper strut
El 7
nose
assembly (14).
gear assembly, inflate to 300 psi with
retainer (2) with soapsuds.
dry
air
or
nitrogen
and coat the air valve
assembly (14)
housing
5-63
BEECH BARON 55 AND 58 SHOP MANUAL
WARNING
IWARNINO)
operations involving equipment under high pressure, exercise caution
performing the leak test; avoid the areas directly above and below the strut.
As with all
when
o.
Release the air pressure and clean
p.
Safety
wire the air valve
soapsuds
assembly (14)
off the top of the
nose
when
gear with fresh water and wipe dry.
and install the cap.
CHART5-4
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TE-301
I.D.
ITEM
AND AFTER; TH-1 AND AFTE R)
O.D.
WEAR TOLERANCES AND INSPECTION
PROCEDURES
NOTE
gear components. Where
and outsidepe rti ne nt, th e permissible wear lim its are given fo r those components. All inside-diameter
diameter (O.D.) dimensions are given in inches. Refer to Figure 5-12.
Listed below
I
are
the tolerances used to determine the extent of
Upper Strut Housing
(2) (Hole Diameter)
Retainer
0.3145
0.3120
wear
in the
nose
Visually inspect for wear, damage and corrosion. Any
scratches or worn areas which can not be repaired is
cause for rejection. Conduct fluorescent or dye penetrant
inspection per MIL-STD-6866. Any crack is cause for
rejection. Replace if wear tolerances are exceeded.
Corrosion proof retainer per MIL-C-5541.
in spect torq ue knee assembly for wear, damage
and corrosion. Any scratches or worn areas which can
not be repaired is cause for rejection. If no visible wear is
Visually
Torque Knee Assembly
(18 and 22)
evident, conduct fluorescent
or
dye penetrant inspection
per MIL-STD-6866. Any crack is cause for rejection.
Corrosion p roof as necessa ry pe r M I L-C-5541 a n d to u c h
up
Upper Torque
Knee
Bo re
Bushings (16)
paint
as
required.
(18)
if
0.4698
Replace
0.4683
exceeded.
u ppe r
to rq ue knee we a r to I e ra nces are
bushings and inspect bores for corrosion.
locquic primer (72, Consumable
Materials Chart, Section 2) and install new bushings
using an adhesive (71, Consumable Materials Chart,
Section 2).
Remove all
Coat all bores with
5-64
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
C HA RT 5-4
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TE-301
AND A FTE R; TH-1 AN D AFTE R)
l.D.
ITEM
O.D.
(CONTI N U ED)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Knee Pin
(17)
0.3740
Visually inspect
0.3730
scratches
cause
for
for wear, damage and corrosion. Any
which can not be repaired is
or worn areas
rejection.
If
no
visible
wear
is evident, conduct
a
mag netic particle inspection per M IL-STD-1 949. Any
crack is cause for rejection. Replace if wear tolerances
are
Torque
Knee Center
Hinge
(U ppe r)
Bore
exceeded.
Joint
Replace
0.3760
if to rq ue knee weartolerances
are
exceeded.
0.3740
bushings and inspect bores for corrosion.
locqu ic primer (72, Consu mable
Materials Chart, Section 2) and install new bushings
using an adhesive (71, Consumable Materials Chart,
Section 2).
Remove all
Bushings (21, 25)
Coat all bores with
(Lower)
Bo re
Replace
if to rque knee weartolerances
0.4698
Replace
if lowe r to rq ue knee
0.4683
exceeded.
0.3760
are
exceeded.
0.3740
Lower
Torque
Bo re
(Lower)
Knee
(22)
wear
tolerances
are
bushings and inspect bores for corrosion.
locq uic primer (72, Consu mable
Materials Chart, Section 2) and install new bushings
using an adhesive (71 Consumable M ate rials C hart,
Section 2)
Remove all
Bushings (24)
Coat ail bores with
Knee Pin
(23)
0.3740
Visually inspect
0.3730
scratches
for wear, damage and corrosion. Any
which can not be repaired is
or worn areas
fo r rejection. If no visi ble wear is evident, co ndu ct
magnetic particle inspection per MIL-STD-1949. Any
crack is cause for rejection. Replace if wear tolerances
cause
a re
Strut
Housing (15)
0.1940
0.1840
exceed ed.
Visually inspect for wear, damage and corrosion. Any
sign of scratches or worn areas which can not be
repaired is cause for rejection. Conduct a fluorescent or
dye penetrant inspection per MIL-STD-1966. Any sign of
cracking is cause for rejection. Check the I.D. of bushing
does not exceed
Lower Strut
Bearing (35)
1.757
1.752
E17
a
wear
tolerances.
Visually inspect for wear, damage and corrosion.
Replace if wear tolerances are exceeded.
5-65
BE ECH BARON 55 AND 58 SHOP MANUAL
C HA RT 5-4
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TE-301
ITEM
AND
AFTER;
I.D.
TH-1 AND
O.D.
AFTER) (CONTINU ED)
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Orifice Rod Assembly
(26)
Visually inspect
shows
damage and corrosion. If rod
damage, check for straightness
Conduct a fluorescent or dye
for wear,
no severe wear or
within 0.03 inches.
pe n et ra nt i nspectio n per M I L-STD-6866. If rod is bent
sign of cracking is cause for rejection.
or
any
Piston and Fork Assembly
Chrome Portion
(top)
(40)
1.503
1.750
1.497
1.747
Visually inspect for wear, damage and corrosion. Any
sign of scratches and worn areas which can not be
repaired is cause for rejection. Conduct a magneticparticle inspection per MIL-STD-1949. Any sign of
cracking is cause for rejection. Replace if wear tolerances
are
Upper
Axle
Strut
Bearing (31)
1.751
1.999
1.748
1.998
(41)
1.249
1.248
exceeded
or
plating
is
unacceptable.
Visually inspect for wear, damage and corrosion.
Conduct a magnetic particle inspection per MIL-STD1949. Replace if plating is scratched or worn through.
Visually inspect for wear, damage and corrosion. Any
sign of scratches and worn areas which can not be
repaired is cause for rejection. Conduct a mag neticparticle inspection per MIL-STD-1949. Any sign of
cracking is cause for rejection. Strip and cadmium plate
axle as necessary, per Fed QQ-P-416, Type II, Class 2
o n sc rate h ed or wo rn areas.
Axle
Bearing (42)
Brace
1.258
1.750
1.254
1.745
Visually inspect for wear, damage and corrosion.
Replace if wear tolerances are exceeded.
for wear, damage and corrosion. Any
worn areas which can not be repaired is
Visually inspect
Assembly (6)
scratches
or
rejection. Remove all bearings and inspect for
ion.
Conduct flu o resce nt or dye penetrant
co rros
inspection per MIL-STD-6866. Any crack is cause for
rejection. Coat interior of brace and h i n g e bea ri n g holes
cause
with
for
co rrosion
G rad e 1
or
2.
p reve ntative cc mpo u n d pe r M IL-C-1 61 73,
all bearings when nose gearis
Replace
overhauled.
Hinge Bushings (7)
0.4995
Replace bushings
when
nose
gear is
ove rhau led.
Replace bushings
when
nose
gear is
ove rhau led.
Re p lace b u s h i n gs wh e n
nose
g ea r is
ove rhau led.
0.4980
Bushings (9)
0.3760
0.3745
Bushings (8)
0.501 0
0.4995
5-66
E17
BEECH BARON 55 AND 58 SHOP MANUAL
CHART 5-4
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES
(TE-301
AND
AFTER; TH-1 AND AFTER) (CONTINUED)
I.D.
ITEM
WEAR TOLERANCES AND INSPECTION
O.D.
PROCEDURES
Internal Sea rings
Upper
and Lower
(5
and 1 0)
2.504
Re p lace bea ri n g s whe n
2.502
Align me nt
ream new
nose
bearings
gear is overhauled.
to
specified
wear
tolerances Dri II out I u bricator ho res th rou g h bea ri ngs and
install lubricators.
spacer (4)
Visually inspect for wear, damage and corrosion. If the
coated side (up side) of spacer is worn through replace.
Mi n o r sc ratche s a nd sc uff i n g is acce ptab I e.
Spacer (1 1)
Visually inspect for wear, damage and corrosion. If the
coated side (down side) of spacer is worn through,
replace. Minor scratches and scuffing is acceptable.
Instruction Placards
Do not
remove
inspection
assembly except
replace ment.
from brace
pu rposes
or
for
NOSE GEA R SHIMII/IY DA MPER SER VICING
Service the
shimmy damper.
Refer to Section 2, SHIMMY DAM PER.
NOSE GEAR SHII~VIY DAMPER REMOVAL
a.
Remove the nut, washers,
bushing
b.
Remove the nut, washers,
bushing,
and bolt which attach the
bolt and
remove
the
shimmy damper
to the gear brace.
shimmy damper from
the barrel/strut.
NOSE GEAR SHIMMY DAMPER INSTALLA TION
shimmy damper
to the barrel/strut.
a.
Install the
bushing, washers,
nut and bolt
attaching
the
b.
Install the
bushing, washers,
nut and bolt
attaching
shimmy damper to the gear brace. For alignment purdamper and the lug on the brace, and a 1 00 951 -X031 -YM
poses, attach a 1 00951 -X031-YN washer between the
washer under the nut.
c.
Swivel the
nose
wheel to check the
the
turning radius of the strut and for freedom of movement without binding or
adjustment bolts to the stop shimmy damper piston 1/32 inch to
gear steering travel
1/4 inch from maximum travel in both directions.
rough spots. Adj ust
the
nose
NOSE GEA R SHII~1MY DAMPER-O VERHA UL
NOTE
Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in Section 15 for time limits and maintenance checks of the
E17
nose
gear
shimmy damper.
5-67
BEECH BARON 55 AND 58 SHOP MAN UAL
NOSE GEAR SHIMMY DAMPER DISASSEMBLY
I
FIGURE 5-13
a.
Remove cotter
or screw
b.
the
driver
so
pin (1),
washer
(8)
that the parts will not
Remove the
floating
floating piston (10).
(10) by
p iston
compression spring (9) by holding the washer (8)
spring out when the cotter pin (1) is removed.
and
eng ag i ng it with
a
long
6-32
sc rew o r
down with
Remove the snap ring (2) and piston scraper (3). Force the barrel end (5) out of the barrel
piston rod (12) back and forth. Remove O-rings (4) from the barrel end (5).
R e move al I
e.
Remove the snap
f.
Insert
a
the forward
re mai n i n g
hyd rau lic
ring (23)
fl u id
by
i nve rti n g sh immy
and slide the
piston
rod
dampe r
(12) with
the
and
small rod
th readed rod. Remove O- ring
c.
d.
a
pumping
the
remaining parts
piston
(1
1
from
the
(6) by working
rod
(1 2).
out of the barrel
(6).
long 6-32 screw or threaded rod into the hole atthe clevis (24) end of the piston rod (12) and engage
floating piston (17). Pull floating piston (17) toward clevis (24) so that the piston retaining pin (15) can
be d rive n-out.
Remove the piston retaining
g.
and remove O-ring (16).
pin (15)
and
the
push
remaining compression spring (18)
O-rings (13) from the damper piston (14).
h.
Remove the
i.
R e m ove re mai n i n g barrel end
f ro m th e barrel end (1 9).
21
(1 9)
and
piston
floating piston (17)
and slide the
scraper
(22)
out the open end of the
damper piston (14) off the piston
from the
piston
rod
(1 2).
Remove
piston
rod
(12).
rod
(12)
Remove
O-rings (20
and
NOSE GEAR SHIMMY DAMPER CLEANING, REPLACEMENT PARTS AND REPAIRS
CLEANING
Clean all
parts with cleaning solvent (1 5, Consumable Materials
C h a rt, Secti o n
2).
Rinse and d ty tho roug hly afte r
cleaning.
CAUTION 1
ICAVTION
For
replacemen t,
Lubricate all internal parts with
use
O-rings approved
hydraulic
fluid
(13,
for
use
with mineral base
hydraulic
Consumable Materials Chart, Section
fluid.
2) prior to assembly.
REPLA CEMENT PA R TS
I
F’e URE 5- 13
a.
Inspect all parts and assemblies for damage
Wear which is
greater than the allowable
Damage which
Parts that
are
cannot be corrected
cracked, chipped
Parts that have corrosion
5-68
or
or
or
or
wear
excessive
wear.
The
following conditions
are cause
for
rejection:
tolerances. Refer to Chart 5-5.
repaired.
broken.
other defects that cannot be
repaired.
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
b.
Rep lace
t he fo I lowi n g pa rts whe n
Cotter Pin
(1)
Retaining
Pin
nose
gear
shimmy damper
is overhauled:
(15)
O-Rings (4, 11, 13, 16, 20, 21)
Safety
Wire
Snap Ring (2)
Sp ri ngs (9,
1
8)
Piston Sc ra pe rs
Washer
E17
(3, 22)
(8)
5-69
BEECH BARON 55 AND 58 SHOP MAN UAL
12
14
io
16
17
18
13
I.
2.
3.
4.
5.
6.
7.
8.
9.
IO.
I I
I~.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
COTTER PIN
SNAP RING
PISTON SCRAPER
O-RINGS
BARREL END
BARREL
ATTACHMENT HOLE
WASHER
COMPRESSION SPRING
FLOATING PISTON
O-RING
PISTON ROD
0-RINGS
DAMPER PISTON
RETAINING PIN
15
19
20
21
O-RING
FLOATING PISTON
COMPRESSION SPRING
BARREL END
O-RING
O-RING
PISTON SCRAPER
SNAP RING
CLEVIS
23
24
C94E03282874
Shim my
Damper
Figure 5-13
5-70
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
REPAIRS
a.
Visually inspect casting
and
wear.
cessively
b.
All
for cracks and
pitting; and finished su rfaces for scoring, pitting, nicks, cracks, disto rtion
determining the extent of wear. Replace all defective and ex-
Refer to Chart 5-5 for tolerances to aid in
wom
parts
or
parts.
assemblies may be
repaired
if any of the
of shafts may be corrected
Slight scoring
following problems
by lapping carefully
with
exist:
flat oil stone.
a
NOTE
Do not exceed 10% of the component material thickness when
removing nicks,
burrs and scratch-
es.
Smooth minor nicks, burrs, and scratches.
as
Those parts that are scratched or have worn
or be replaced with new parts.
plating
may be
stripped
and
replated
with the
same
type of plating
that removed
Minor thread
damage, chase
to clean or smooth.
NOTE
damage requires inspection to determine the depth of penetration and the cross-sectional area change. The damaged area must be tho roug h ly cleaned and the corrosion must be removed. The deterioration caused by corrosion or removal of corrosion must not reduce the material
thickness of any component by more than 10%. Refer to Chart 5-5 for NOSE GEAR SHIMMY
Corrosion
DAM PERWEAR TOLERANCES A N D I N S P ECT I O N P ROC E D U RESon
tional information contact the Technical
Box 85,
Wichita, KS
plate
per Fed
Bushings
applicable, and apply
QQ-P-416, Type II.
that check within allowable
When evidence of
Raytheon
com po n e nts. For ad d i
Aircraft Company, P.O.
I
67201.
Remove corrosion if
mium
Support Department
of
damage
corrosion
wear
prevention
tolerances may be
exists to steel parts,
materials
as
necessary per MIL-C-5541
or
cad-
re u sed.
magnetic particle inspect
per MIL-STD-1949.
NOTE
Do not
remove
paint
or
primer from
the
area
to be fluorescent
or
dye penetrant inspected per
MIL-
ST D-6866. If the fi n is h abso rbs the penetrant so that bleed out prevents satisfactory inspection or
if a new finish has not cured for at least 30 days, contact the Technical Support Department of Ray-
theon Aircraft
Company,
When evidence of
damage
I
P.O. Box 85, Wichita, KS 67201.
exists to metal parts other than steel, fluorescent penetrant
inspect
per MIL-STD-
6866, Type I.
Replace damaged
E17
or
unserviceable parts with
new or
serviceable parts.
5-71
BEECH BARON 55 AND 58 SHOP MANUAL
NOSE GEAR SHIMMY DAMPERASSEMBLY
I
F’ GU RE 5-13
a.
rod
Replace
(12).
the
O-rings (20
and
21)
on
the barrel end
(19).
Slide the
piston
scraper
(22)
and barrel end onto
piston
Replace the O-ring (16) on the floating piston (17) and insert the compression spring (18) and the floating piston
piston rod (12). With a long 6-32 screw or threaded rod, engage the floating piston (17) by pulling it toward
the clevis (24) so that the retaining pin (15) can be inserted. Install the damper piston (14) on the piston rod (12) and
insert the retaining pin (15). Replace the O-rings (13) on the damper piston (14).
b.
into the
c.
Insert the
piston
rod
and components into the barre 1
(12)
(6)
and
place
the snap
ring (23)
into
position.
(6) in a vise with the open end up and fill the barrel (6) and piston rod (12) with h yd ra u lic fl u id
Materials Chart, Section 2). Work the piston rod (12) up and down until bubbles stop appearing in
the fluid, then refill the barrel (6) and the piston rod (12). To eliminate the possibility of an air pocket under the barrel
end (5), ensure that the barrel (6) is completely full of hydraulic fluid. Any excess fluid will be forced into the piston
d.
Place the barrel
(13, Consumable
the barrel end
(5)
rod
(12)
e.
Replace the O-rings (4)
and
secure
f.
Pill the
as
with snap
piston
with
(17)
(10) down
ton
a
is inserted.
on
the barrel end
(5).
Insert the barrel end
(5)
and
piston
scraper
(3)
into the barrel
(6)
ring (2).
(12) with hyd rau lic fluid (1 3, Consu mable Materials Chart, Section 2). Engage the floating pislong screw and pull towards the clevis (24). At the same time, insert and push the floating piston
piston rod (12). This will cause hydraulic fluid to be sucked into the piston rod (12) and preventing
rod
6-32
into the
the entry of air.
compression spring (9), washer (8)
remove from the assembly.
g.
Install
(17)
and
h.
Check the fluid level in the
secure
(12).
piston
(10) exceeds 2-3/16 inches,
i.
Install
shimmy damper on
with cotter
remove
nose
the
pin (1).
Release the 6-32 rod from the
piston
pin (1) and inserting a 1/16 inch diameter
floating piston (10). If the distance to the piston
top
and
add more fluid to the piston rod (12).
floating piston (10)
shimmy damper by spreading
Measure the distance to the
rod
wire into the
rod
and
the cotter
of the
gear of the airplane, refer to NOSE GEAR SHIMMY DAMPER INSTALLATION
in this Section.
j.
Service the
5-72
shimmy damper
as
described under the
heading
SHIMMY DAMPER in Section 2.
E17
BEECH BARON 55 AND 58 SHOP MANUAL
C HA RT 5-5
NOSE GEAR SHIMMY DAMPER WEAR TOLERANCES
A N D I N S PE CTI O N PROCEDURES
I.D.
ITEM
WEAR TOLERANCES AND INSPECTION
O.D.
PROCEDURES
NOTE
Listed below
and outside-diameter
Barrel
(O.D.)
dimensions
wear
are
Visually inspect for wear, damage and corrosion.
Replace if wear tolerances are exceeded.
0.3765
0.3745
0.857
Damper Piston (14)
0.850
Floating
Pistons
(10
and
0.240
17)
0.232
Piston Rod
(1 2)
0.253
0.246
are
Visually inspect for wear, damage and co rrosi on. Any
sign of scratches or worn areas which can not be
repaired is cause for rejection. If localized damage exists,
conduct a fluorescent or dye penetrant inspection per
MIL-STD-6866. Any sign of cracking is cause for
rejection. Replace if wear tolerances are exceeded.
0.860
(7)
limits
given
0.865
(6)
Attachme nt Ho le
wear in the nose gear shimmy damper
g iven fo r those co m po ne nts. Al I i n s i d e d ia mete r
in inches. Refer to Figure 5-13.
the tolerances used to determine the extent of
are
components. VVhe re pe rti ne nt, th e permissible
Visually inspect for wear, damage and corrosion.
Replace if there is any noticeable ridges or grooves at
0-ring seats. Replace if wear tolerances are exceeded.
Visually inspect for wear, damage and corrosion.
Replace if there is any noticeable ridges or grooves at
O-ring seat. Replace if wear tolerances are exceeded.
ins pect fo r strai g htness,
0.3745
Visually
0.3725
corrosion
be
or worn areas.
repaired
tele rances
Clevis
is
cause
are
for
c
racks, scratch es,
Any signs of wear which can
rejection. Replace if wear
not
exceeded.
Visually inspect for wear, damage and corrosion.
cadmium plate as necessary per Fed QQ-P-416, Type II,
(24)
Class 2.
Bo re
Slot
Barrel Ends
(5
and
for any sign of
exceeded.
wear.
Replace
if
wear
any sign of
exceeded.
wear.
Replace if
wear
0.1 96
Visually inspect
0.190
tolerances
0.198
Visually inspect for
0.1 93
tele rances
are
are
Visually inspect
Corrosion proof
19)
for wear, damage and corrosion.
with Alodine (54, Consumable Materials
Chart, Section 2)
Hole Diameter
E17
0.379
Visually inspect
0.376
tele rances
are
as
for
required.
wear or
damage. Replace
if
wear
exceeded.
5-73
BEECH BARON 55 AND 58 SHOP MANUAL
NOSE GEA R RETRA CT R/IECHA NISI1I1 SER VICING
NOSE GEAR RETRACT BRACE ASSEMBLY CHECK
THRU TC-2091, TE-938, AND TH-1 THRU TH-871 WITH BEECH KIT NO, 35-4012-1 INSTALLED;
TC-2092 AND AFTER; TE-1114 AND AFTER; AND TH-872 AND AFTER)
(TC-1608
FIGURE 5-14
a.
C heck
o utboa rd arm
(20), inboa rd arm (21 attachment bolts (22), washers (23) and nuts (24) for security.
(59) and (90) for indications of cracking and the mechanism assembly for shear stress,
Check retract rod rod-ends
wear
and/o r
co rrosion.
Refe r to Section 16 for scheduled service and mai ntenance checks.
Tighten any loose hardware and replace all hardware that show sig ns
cracking. Clean area of any corrosion before installing hardware.
b.
5-74
of shear stress, wear, corrosion and/
or
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
36
35
34
1
st
31
30
32
33
38
A
40
41
39
38
41
1~
20
37
21
37
B*
9
41
40
39
38
25
38
U
13
22,
1
~,Y
23,
26
27
24
19
14\
DETAILB
15
11
17
16
28
ha
DETI~TLA
h ~7
5
3
25.
BOLT
26.
WASHER
27.
BUSHING
28.
WASHER
29.
NUT
30.
DOOR
ACTUATOR
SHAFT
13
AFT
14.
DOOR
15.
SCREW,
WASHER
16.
BOLT,
WASHER,
NUT
34.
SCREW
5.
NUT
17.
BOLT,
WASHER,
NOT
35.
NUT
18.
DOOR
ACTUATOR
PIN
36.
ROD
19
BUMPER
37.
DOOR
1.
RETRACT
BRACE
2.
RETRACT
DRAG
3.
BOLT
4.
ASSEMBLY
LEG
ASSEMBLY
DRAG
BRACE
WASHER,
6.
COTTER
LUBE
8.
BOLT
20
OUTBOARD
9.
BUSHING
21.
INBOARD
PIN
FITTING
AND
BUSHING
BRACKET
ACTUATOR
7.
ASSEMBLY
AND
PIN
SUPPORT
NUT
ASSEMBLY
31.
SCREW
32.
NUT
33.
SPRING
END
ACTUATOR
ASSEMBLY
ROD
ARM
ARM
38.
BALL
ASSEMBLY
JOINTS
10.
BUSHING
22.
BOLT
39.
WASHER
11.
WASHER
23.
WASHER
40.
NUT
12.
NUT
24.
NUT
41.
NUTS
Tote
992895RR´•RI
Nose Gear Retract Mechanism
After; TE-1114 and After; TH-872 and After; and TC-1608 thru TC-2091,
TE-938, and TH-1 th ru TH-871 with Beech Kit No, 35-401 2-1 installed)
(TC-2092
and
Figure
E17
5-14.
(Sheet
1 of
3)
5-75
BEECH BARON 55 AND 58 SHOP MANUAL
43.
RETRACT
44.
BOOT
45.
STUD
ROD
BOOT
RE~IIAINING
ASSEMBLY
RING
46.
CABLE
47.
RETRACT
48.
STRIP
49.
STUD
50.
CABLE
51.
COVER
52.
SCREW AND WASHER
53.
RETRACT
54.
BOLT
55.
WASHER
56.
NUT
TIE
ROD
BOOT
TIE
57.
COTTER
58.
TUBE
61.
WASHER
62
NUT
63
RETRACT
64
BOLT
65.
WASHER
66.
NUT
67.
COTTER
68.
BRACKET
AFT
ROD
A
ASSEMBI~
53
PIN
/~541
69.
COLLAR
70.
WASHER
IDLER
ARM
ASSEMBLY
72
PIN
6,8
71.
FL~HEAD
72.
COTTER
73.
IDLER ARM
74.
BUSHING
75.
BEARING
76.
BUSHING
74,7i
PIN
f
63
PIN
´•´•~i
70
/Ia
69
71
68
~e
fi
66
B
"1
65
64
65
50
46
4~7
d
4~8
43
~Y
P~B
I
r’, I
65
44
Q2
P’-- 57
I
58
51
QsI~- 5 6
Vi~n
f
49
Y--
55
59
61,b
45
DETAIL
A
TC328
992896RRAI
Nose Gear Retract Mechanism
After; TE-1114 and After; TH-872 and After; and TC-1608 thru TC-2091,
(TC-2092
TE-938, and TH-1 thru TH-871 with Beech Kit No. 35-4012-1 installed)
and
Figure
5-76
5-14.
(Sheet
2 of
3)
E17
BEECH BARON 55 AND 58 SHOP MAN UAL
77.
RETRACT
78.
BOLT
79.
NUT
80.
COTTER
81.
ROD
82.
RoD
83.
PLUNGER
84.
SPRING
LINK
FORWARD
ROD
ASSEMBLY
PIN
ASSEMBLY
85.
SMEAR
86.
WASHER
87.
COTTER
88-
NUT
89.
WASHER
I~U1
ASSEMBLY
PIN
B
PIN
77
90.
ROD
91.
WASHER
92.
WASHER
93.
RETRACT
END
ROD
LINK
DECAL
80
79
90
/I
1~1I
78
,9’
85
fi
88
89
92
91
82
86
84
87
i
81
DETAIL
7
A
8;
/o
0~
E3
8
DETAILB
Q
Tclze
992897RR.RI
Nose Gear Retract Mechanism
and After; TE-1114 and After; TH-872 and After; and TC-1608 thru TC2091,
TE-938, and TH-I th ru TH-871 with Beech Kit No. 35-4012-1 installed)
(TC-2092
Figure
E17
5-14.
(Sheet 3
of
3)
5-77
B E EC H BARON 55 AND 58 SHOP MAN UAL
REMO VING A ND INSTALLING THE LA NDING GEA R A CTUA TOR A SSE~BL Y
a.
Remove the cabin front seats.
b.
Remove the
c.
Disconnect the main
d.
Remove the
e.
Remove the four
and
move
f.
Disconnect the
g.
Remove the
access covers on
flap
the switch
landing
top and directly behind the front carry through
gear retract rods at the actuator.
mote r attac h i ng bolts and disconnect the
landing
gear door
securing the landing gear limit switch assembly
assembly aside to permit removal of the actuator.
screws
gear motor electrical
landing
structure.
landing gear actuator access
linkage from the actuator.
on
actuating
rods at the actuator.
the left hand side of the actuator
wiring.
door
on
the bottom of the
fuselage,
and
remove
the
nose
gear actu-
ator retract arm and
h.
Remove the fo u r actuate r attach ing nuts and
i.
installation is
a reverse
certain that the index mark
Make certain that the
j.
remove
the actu ato r.
of removal. When installing the nose gear actuator retract arm
the arm coincides with the index mark on the actuator shaft.
on
the actuator, make
on
landing
gear limit switch actuators
are
installed when the retract rods
are
connected to the
actuator.
k.
Install cotter pins and
i.
After
completing
the
safety
landing
wire.
gear actuator installation, check the
landing
gear for proper
rigging.
LANDING GEAR A C TUA TOR O VERHA UL
I
Fle URE 5- 15
a.
Remove the motor
b.
Remove the snap
(1)
from the actuator and
ring (3)
remove
from the end of the shaft
the gear
(19)
and
(2)
from the face of the motor.
remove
the gear
(4)
from the shaft.
Remove the snap ring (5) from the end of the actuator drive shaft (7) and remove the actuator retract arm (6)
c.
from the shaft. On all aircraft except as noted below, push the shaft out of the assembly in the direction of the arrow.
NOTE
On aircraft serials TC-538 thru TC-541, TC-585, TC-589, TC-590 thru TC-595 and TC-612 the actuator drive shaft (7) and the actuator worm sector (1 0) are a one-piece unit and may be. re moved
by separating the
d.
Remove the
gear
e.
screws
(8)
all maintenance
housing.
With this
exception,
from around the
housing,
also the bolt
actuator
procedures
(9). Separate the housing
are
and
the
same.
remove
the sector
(10).
Remove the
screw
(Il)from
the actuator hand crank
(12)
and
remove
the
spacer(l3)
and
6-ring (14)
from the
shaft.
f.
Remove the
ator
housing.
5-78
screws
(15)
from the hand crank
housing (16)
and
remove
the hand crank
housing
from the actu-
617
BEECH BARON 55 AND 58 SHOP MANUAL
g. With a lug spanner wrench, remove the retainer nut (17) from the actuator housing. Tap out the shaft (19) in the
direction of the arrow. Remove the cotter pin and back off the lock nut (21). Slide the bearing (20) down the shaft
until the two sections of the half
the seal
(22)
out of the actuator
Remove the
i.
Remove the seal
j.
Remove the snap
k.
Remove the
(25)
may be removed. The
bearing
and
24) from the
actuator
and the
bearing (26)
from the top and bottom
bearings (23
h.
ring (18)
housing.
ring (27)
bearing (29)
from the shaft
from the
(7)
can now
be removed from the shaft. Drive
housing.
and slide the
nose
housing
halves.
gear actuator retract
arm
(28)
off the shaft.
housing.
Clean all parts in solvent removing the grease and oil. Check all bearings for cracks and wear. Check the teeth of
the sector gear for cracks and wea r. Re place pa rts as necessary. Replace all seals at reassembly. Seal the upper
and lower hous i ng jo i nts using silastic sealer (5, Sealing Chart, Section 2). Reassemble the actuator in the reverse
procedure. Remove the filler plug (30) from the actu ato r h o u s i n g and fi I I the housing with 1/2 p i nt of
gear grease (10, Consumable Materials Chart, Section 2). Before attaching the motor, pack the motor gear housing
with app roxi mate ly one ounce of grease (8, Consumable Materials Chart, Section 2). (Fiil within +0.00 -0.1 0 i n, of
the housing center line.)
I
of the above
NOTE
At
assembly
marks
on
installing the actuator drive shaft through the sector gear make sure the scribe
piece match. The same applies when installing the nose gear actuator retract arm
when
each
and the main actuator retract
E17
arm on
each end of the actuator drive shaft.
5-79
I
BEECH BARON 55 AND 58 SHOP MAN UAL
oo
s
a
~cls
~I
20
a
13
i.
Motor
2.
3.
Spur and Pinion
Snap Wng
4.
Wo rm Drive Cea r
5.
6.
Snap Ring
Gear
15-~a
7.
8.
Screw
25
~F3,
RW~
~jil,
Bolt
Screw
13.
14.
15.
16.
Spacer
"0" Ring Seal
Actuater Hand Crank
R
~c2
Screw
Hand Crank Shaft
a
Housing
17.
Retainer Nut
18.
Hall-ring
---J~
Q
19.
Worm Gear
26.
Bearing
20.
Bearing
27.
Snap Ring
21.
22.
Lock Nu t
2 8~
Ac tuator Re tra ct A r m
Seal
29.
Bearing
Rearing
Bearing
30.
Grease Fill
24.
3 1.
Ba ii C hec k
25.
Seal
32.
Sector Gear
33.
Spae er
u?
Plug
21
Stop Assy.
Landing
27
rHose
ss~755nn
Gear Actuator
Figure
5-80
~----22
26
Actuator Worm Sector
11.
12.
23.
2(
35
Actuator Re tract A rm
Ac tuator Drive Sh aft
9.
10.
10
Assembly
5-15
El 7
BEECH BARON 55 AND 58 SHOP MANUAL
REMO VING AND INSTALLING THE LA NDING GEAR MOTOR
a.
Remove the
rig ht
front seat.
b.
Remove the
access
c.
Disconnect the electrical
d.
Remove the three
landing
e.
Install the
gear motor
landing
plate
over
the motor.
at the
wiring
gear motor
landing
gear
attaching
by reversing
dynamic
bolts and
brake
remove
the above removal
relay.
the
landing
proced u re
and
gear motor.
safety
the three
attaching
bolts.
REI~IO VING A ND INSTALLING THE LA NDING GEAR DYNAMIC BRAKE RELA Y
a.
Remove the
right
front seat.
b.
Remove the
access covers on
c.
Disconnect the electrical
d.
Remove the two
e.
Reinstall the
top and directly behind the front carry through
wiring
dynamic
brake
at the
brake
dynamic
relay attaching
dynamic brake relay by reversing
structure.
relay.
and
screws
remove
the above removal
the
dynamic
procedure
brake
relay.
and check
rigging.
NOSE WHEEL STEERING MECHANISM
The
wheel should be parallel to the fore and the aft ce nte r ii ne of the airplane with the rudder pedals in the
position. Take the nose gear steering actuator arm loose at the back end and screw the end fitting either in
to make the adjustment.
nose
neutral
or
out
NOSE WHEEL TRA VEL S TOP A DJUS TMEN T
The travel stop must be adjusted
maximum travel. If adjustment is
a.
Loosen the lock nuts
b.
Turn the
wheel in this
nose
the
the
nose
required
the
adjustment
wheel travel is
stopped when the shimmy damper
following proced u re is reco m mended:
bolts until
wheel to the extreme left turn
they
position.
clear the stops
The
on
the
adjustment bolts
nose
wheel
must clear the
is 1/32 inch from its
straightene r.
stops with the
nose
position.
tape around the aft end of the shimmy damper piston rod 1/32 inch from the scraper ring.
c.
Place
d.
Turn the lock nuts
tacts the scraper
Tum the
e.
on
so
adjustment bolts so the
ring. Tighten the lock nuts securely.
nose
on
the
wheel to the extreme
right, place
nose
wheel is turned and the tape
the tape
LANDING GEAR POSITION LIGHT ADJUSTMENT
on
(TC-1608
the forward end of the
on
the
piston
piston
rod
just
con-
rod and repeat step d.
AND AFTER; TE-938, TE-943 AND AFTER;
TH-385 A N D A FT E R)
landing gear
indicator switches
The
positio n lig hts
on
on
panel are controlled by the U P indicator switches and DOWN
airplane
jacks, adjustment of these switches may be made as follows:
the instrument
each gear. With the
on
MAIN GEAR
a.
so
With the gear down and locked, adjust the DOWN switch (located on the forward side of the main gear V brace)
that the overtravel of the switch plunger is 0.050 inch after the switch is actuated to the ON pos iti on. W it h t he
E17
5-81
BEECH BARON 55 AND 58 SHOP MANUAL
gear in the full up position, adjust the UP switch (located inboard of the forward side of the main gear V
that the overtravel of the switch plun ger is 0.050 inch after the switch is actuated to the ON position.
brace)
so
NOSE GEAR
With the gear down and locked, adjust the DOWN switch (iocated on the right side of the wheel well) so that the
overtravel of the switch plunger is 0.050 inch after the switch is actuated to the ON position. With the gear in full up
a.
pos ition, adj ust the UP switch (located on the right side of the wheel well) so that the overtravel of the plunger is
0.050 inch after the switch is actuated to the ON position. Check the instrument panel to be sure the indicator lights
correspond
b.
to the gear
position.
Recheck the switch
adjustment,
then
remove
the
airplane from
the
THROTTLE WA RNING HORN S WI TCH A DJUS TMENT
Adjustment
a.
of the throttle
With the
airplane
in
warning
horn may be
flight, place
the
accomplished
propeller controls
as
jacks.
(TC-I A ND AFTER)
follows:
in the low
pitch position
and
slowly
retard the throttle
con-
trols until 12 to 1 4 inches of manifold pressu re is i nd icated.
b.
Mark the
position of
c.
After the
airplane
the throttle controls.
has landed and with the
engines
shut off,
position
the throttle controls at the
ma rk m ade
in
step b.
d.
as
e.
Adjust the phenolic blocks on the threaded linkage
by an audible click.
behind the instrument
panel
until the switches actuate closed
indicated
Secure the blocks in this
position.
THROTTLE WA RNING HORN S WITCH ADJUSTMENT
(TE- 1
A ND A FTER; TH- I THRU
TH- 1 542 AND TH- 1544)
Adjustment
a.
of the th rottle warni ng horn may be
With the
airplane
in
flight, place
the
acco
mpl is hed
propeller controls
as
fo I I ows:
in the low
pitch position
and
slowly retard
the throttle
con-
trols until 12 to 14 inches of manifold pressure is indicated.
b.
Ma rk the
position
of the throttle controls.
c.
After the
airplane
has landed and with the
step
d.
engines shut off, position the throttle
controls at the
ma rk
mad e i n
b.
Adjust the
microswitch in each
engine compartment until the switch
is actuated closed
as
indicated
by an
audible
click.
e.
Secure the switch in this
position.
THROTTLE WARNING HORN AND LIGHT S YS TEM ADJUS TMENT (TH- 1 543, TH- 1 545 AND
AFTER)
The system is designed for the landing gear warning horn to sound intermittently and for the red gear-up annunciator
light to flash with the landing gear retracted and either or both throttles retarded to obtain approximately 13 +1 inches
of Hg in manifold pressure. The warning horn and light are also actuated when the flaps are fully down and the land-
ing gear
5-82
is retracted.
System adjustment
is
as
follows:
E17
BEECH BARON 55 AND 58 SHOP MANUAL
a.
With the
airplane
in
flight
and the
landing
gear retracted, retard the throttles to obtain 13 +1 inches of
Hg
in
man-
ifold pressure.
NOTE
Make all
b.
Mark the
position
of the throttle controls
c.
After the
airplane
has landed and the
to the marks made
d.
on
the
pedestal
adjust
so
position matches the marks made
securing the cam in this position.
trol
e.
on
the
engines
same
altitude and
airspeed.
pedestal.
have been shut down, match the
position of each throttle control
pedestal.
Loose n the retai n ing nuts and
switch j ust forward of the
checks at the
subsequent
Check the switches for proper
each
respective actuator rod for the throttle warning
(ind icated by a click) at the point where the th rottle con(see Figure 5-16 for switch identification). Tighten the retaining nuts
cam on
the end of its
that the switch closes
in step b
operation
in
flight
as
LANDING GEA R- UP INTERRUPT CIRCUI T
desciibed at the
(TH- 1543,
beginning
of this section.
TH- 1545 AND
AFTER)
airplanes are equipped with switches actuated by th rottle position to interrupt the landing gear-up circu it to
prevent the land i ng gear from retracting whe n the th rottles are retarded below 1 5 +2 -1 inches of Hg in manifold
These
pressure.
E17
5-83
I
BEECH BARON 55 AND 58 SHOP MANUAL
THRO TTLE WARN
SW. ACTUATOR ROD
RETRACT-PREVENT
SWITCH
ACTUATOR RODS
LEFT
THROTTLE
RIGHT THROTTLE
III 11 It
WARNING
WARNING SWITCH
III 11 II
SWITCH
RIGHT
LEFT GEAR
GEAR
rr
RETRACT-’
PREVENT
r1~1
RETRACTPREVENT
SWITCH
SWITCH
RETRACT-PREVENT
I ]\THROTTLE
SWITCH CAMS
WARNING
Q
CAMS
DETAIL
A
A~l
LEFT THROTTLE
WA RN ING SW ITC H
LEFT THROTTLE
WARN ING SWI TC H
ACTUATOR ROD
RIGHT THROTTLE
QbWilT~ YB~
O
WARNING SWITCH
ACTUATOR ROD
LEFT THROTTLE
WARNING SWITCH
CAM
55-158-31
Throttle
5-84
Warning
Horn
land Light) and Gear
Figure 5-16
Retract Prevent Switches
E17
BEECH BARON 55 AND 58 SHOP MANUAL
GEAR-UP INTERRUPT CIRCUIT ADJUST~ENT
airplane in flight at a speed between 100 to
rpm, then slowly retard the throttle controls to obtain 15
a.
With the
b.
Mark the
c.
After the
marks made
position
of the throttle controls
on
the
110
(TH-1543,
TH- 1545 AND
AFTER)
knots, place the propeller controls fully forward
+2 -f inches of
Hg
to
high
in manifold pressure.
pedestal.
airplane has landed and the engines have
the pedestal in the preceding step.
been shut down,
position
the throttle controls to match the
on
retaining nuts and adjust each cam on the end of the actuator rod for each mt ract- p reve nt switch
just forward of the pedestal so that the switch closes (indicated by a click) at the point where the throttle control position matches the marks made on the pedestal (see Figure 5-16 for switch identification). Tighten the nuts securing
the cam in this position.
d.
e.
Loosen the
Check the switches for proper
operation
With the
2.
Place the
3.
Advance either throttle control
landing
flight
as
follows:
gear down, retard both throttle controls to
1.
landing
in
landing
gear in the UP
gear should retract with
only
position;
landing
position
below the switch
setting.
gear should not retract.
landing gear retracts.
functioning properly.
note the manifold pressure at which the
slowly and
one
the
a
th rottle control advanced if the system is
The
NOTE
The system circuit includes a latch ing relay that enables the landing gear to fully retract
traction is initiated. Retarding the throttle control should not stop the gear in mid-travel.
once re-
TROUBLESHOOTING BRAKE SYSTEM
1
Solid
pedal and
no
b ra kes.
REMAR KS
PROBAB LE CAUSE
INDICATION
a.
Brake
lining
worn
beyond
a.
Replace lining.
a.
Bleed brake system.
a.
Visually
allowable limit.
2.
Spongy
brake,
3. Unable to hold pressure,
a.
Air in
a.
Leak in brake system,
system.
check entire system for
evide nce of leaks.
b. Check master
rep I ace if
4.
Parking
5. B rakes
brake will not hold.
grab,
a.
A i r i n syste m.
b.
Faulty parking
a.
Stones
or
brake valve.
fore i gn matter
locking
cylinder seals,
sco red.
a.
B le ed b rake syste m.
b.
Replace
a.
Clean brake disc and
b.
Replace
the valve.
lining.
brake disc.
b.
E17
Warped
or
bent disc.
disc.
5-85
I
BEECH BARON 55 AND 58 SHOP MANUAL
TROUBLESHOOTING LANDING GEAR ELECTRICAL SYSTEM
1
Landing gear
R EMAR KS
PROBABLE CAUSE
INDICATION
motor fails to shut
a.
U p-limit switch out of
b.
Faulty
switch.
a.
Safety
switc hes not
b.
Up-limit switch remaining
a.
Down-limit switch does not open,
b.
Faulty
a.
Limit switch out of
adj ustment.
switch.
a.
Adj ust
b.
Replace
a.
Adj ust switches.
b.
Replace
a.
Adj ust
b.
Replace
a.
Adj ust
b.
Replace switch.
a.
Check contin uity.
off when gear is retracted.
2.
3.
Landing gear fai is
Landing gear
to retract.
motor fails to shut
closing.
open,
switch.
limit switch.
limit switch.
off when g ea r i s exte nd ed.
4.
Landing gea r
actu ato r is
hitting
down-limit switch,
adjustment,
limit switch.
I i mit switch.
inte mal stops.
b. Limit switch is
5.
Warning
horn
an n u nciato r
or
GR UP
lig ht ton
a.
Open
or
inoperative.
grounded
circuit.
ai rplane
serials TH-1543, TH-1545 and
after) inoperative
or
malfunctioning.
b. Throttle switches
6.
Landing gear fails
to extend.
inoperative.
b. Check and
adj ust
as
necessary.
adjust
as
necessary.
c.
Flap switch inoperative,
c.
Check and
a.
Tripped circuit
breaker.
a.
Reset circuit breaker.
b. Down-limit switches open.
b. Check down-limit switches, with
the gear retracted the down-limit
sw itc hes s ho u I d be c I osed.
c.
Open
circuit.
c.
Run
continuity
a
check
on
the
down-limit switch.
d.
Landing
gea r mote r
inope rative.
d. Check
replace
7.
Landing gear
will not retract
or
a.
Faulty
electrical connections.
a.
Run
a
system
extend.
b.
Landing
gear motor not
brushes, overhaul
or
motor.
continuity check between
co mpo n e nts.
b. Check motor
ground.
g rou nded.
c.
Faulty control
d.
Landing
circuit.
gea r mote r i n o pe rative.
c.
Check items 1
3.
d. Check brushes, overhaul
replace
5-86
through
or
motor.
E17
SECTION
POVVERP LANT
Ci~)eechcraft
BARON 55 AND 58
SHOP MAN UAL
POWER PLANT
NOTE
It is more practical to remove the four
bolts from the engine vibration isolator
mounts than to remove the bolts from
the mount and firewall. If the bolts are to
be removed from the vibration isolator
mounts, note the position and num ber of
plates and the thickness of the plates on
each side of the engine m ou nt. Tag the
plates fo r id entificatio n at reinstallation.
Refer to Figures 6-1 and 6-2.
ENGINE REMO VA L
CAUTION
The
engine air for the Baron TE serials
supplied through an overhead induction air scoop on the engine cowling.
Care should be taken when removing or
installing the engine that no foreign
objects, dirt, etc., be allowed to enter the
is
h.
Remove the bolts
nacelle firewail
air valve.
Remove the upper and lower cowl, cowl
uator and fillets.
i.
flap
Remove the
act-
plane,
wire to the switch lead at the filter
of the magneto
spark plug
or
a.
Connect
the
engine.
b.
Hoist the
Remove the
c.
Disconnect all
propeller. (See
Section
engine
into
were
tag
controls. Note the
Disconnect the electrical
wiring
at the
all wires and tag them for
ease
position
firewall, or
position of
of reinstallation.
stand under the
opposite wing´• and
position
on
the
lifting ring
of
airplane.
engine
removed
I nstall the bolts
securing the engine to the
plane. (if applicable see Figures 6-1 and 6-2.)
them for ease of reinstallation.
at the accessories as necessary. Note the
a
stand und er the tail.
g. Position the engine hoist and attach the hoisting
hook to the engine lifting ring. Remove slack from the
cable.
515
engine
to the
vibration isolator mounts
during removal, check the
notes made during removal for the number and location of the plates.
7.)
c.
Disconnect the
wing
engine hoist hook
NOTE
plumbing at the firewall. Note the
plumbing and tag each line for ease of
of the controls and
a
an
leads.
reinstallation,
Place
installing the engine to the airplish an inspection in
accom
disconnect all the
If the
b.
f.
to the
engine
accordance with Service I nst ruction No.
0396-241, Rev. 1.
capacitor and ground the wire to the
engine case. If grounding is impractical
remove the cable outletplate on the rear
e.
the
NOTE
To be safe, treat all magnetos as hot
whenever the ground lead is disconnected. To ground the magneto, connect
d.
mou nt
holding
ENGINE INS TALLA TION
Prior to
of all
engine
engine.
CAUTION
position
the
the bolts
to the vibration isolators.
a.
a
holding
or remove
air-
NOTE
When reinstalling the engine mount to
the firewall on serials TC-1 thru TC-244,
torque the nuts on the engine mou nt
frame bolts between 265 and 290 inchpounds. On serials TC-245 and after,
TE-1 and after, TH-1 and after and and
those airplanes complying to Service
Bulletin, No. 1, Revised June, 1962, torque the nuts on the engine m ou nt frame
bolts to 400 ~15
inch-pounds.
6-1
~Z)eechcraft
BARON 55 AND 58
S HOP MAN UAL
To avoid
assure
bottoming out of the nut and
proper tightening of the nut,
to
g.
Connect the
a
h.
Install the
maxim um of th ree AN960-61 6 washers
may be installed for each bolt installa-
plum bing
at the firewall.
prepeller (see Section 7).
t~
CAUTION
tion, using
one washer under the bolt
head and two washers under the nut.
Because the
cowling is an integral part
cooling system, the engine will
overheat if operated with the cowling
NOTE
of the
If the engine is disconnected at the engine shock mounts (vibration isolators),
rather than at the fi rewall, on reinstallation torq ue these engine mount bolts to
removed for
323 ~t25 in ch-poun ds
on TC-1 and after
and torque to 475 +25 inch-pounds on
TE-1 and after and TH-I and after. Be
carefu I to align the holes in the rubber
mount bushings (piates) with the index
pin which protrudes eq uid istantly on
both sides of the steel bushing.
if the fuel
the hoist away from the airplane.
Connect the electrical wi ri ng at the fi rewal I
f.
engine lifting ring
or
at
line nuts at the noule are removed
the 10-520 engine, they should be
or
nuts at
40
45
cylinder head temperature bulb may be located in
of two locations, depending on the engine model.
On the 1O-470-L engines the tem pe ratu re bulb is
one
controls to the
engine.
2
I.
2.
3.
4.
5.
6.
injector line
retorqued to
The
necessary.
engine
very brief test
CYLINDER HEAD TEMPERA TURE BULB
move
Connect the
a
retorqued to 40 45 in. Ibs. The
the manifold valve should also be
in. tbs.
Rem ove the hoist: hook from the
as
injector
from the 10-470
d.
the accessory
than
FUEL INJECTOR LINE NUTS
and
e.
more
period.
4
ENGINE
PLATES
15 EACH)
ENGINE MOUNT
PLATES 13 EACH)
AN960-7 I 6L WASHER
BOLT
r -r rr
I
r~rl-l I II II II II II I I
I it +t tt SC -C-
-U
1
6
I I I I I I I I
~IUU LII
C95TH7180227 9
Figure
6-2
6-1. Lower
Engine
Vibration Isolator Mount
515
BARON 55 AN D 58
SHOP MAN UAL
Push in
located in the lower side of the number five
b.
head. On the 10-520 and 10-550
clockwise.
cylinder
engines the tempera-
ture bulb is located in the lower side of the
two
num ber
head.
cylinder
c.
Connect the
CYLINDER HEAD TEMPERA TURE BULB
d.
tions.
appropri ate
a.
Rem ove the
b.
Remove the wire
cowli ng from th e
engine.
clamp from the engine and wire
bundle.
c.
cover
securing the wires
on
the knurled knob and
rotating
it
coun-
terclockwise.
f.
Pu II the tem perature
bulb from the head.
CYLINDER HEAD TEMPERA TURE BULB
INSTALUI\ TION
a.
Place the tem peratu re bulb in
appropriate
Pull the wire
back
ove r
the wire
connec-
I nsta I I th e clam p around the wire bundle and
attach it to engine.
Install the
position
in the
head.
(Figure
cowling
on
the
engine.
6-4
The th rottle warni ng horn cam and switch are located
on the left side of the engine at the rear of the accessory case on the throttle body. The cam is attached to
the butterfly valve shaft and actuates the switch which
provides power to the warning horn. The switch
adjusted to actuate the landing gear warnhorn
ing
any time the landing gear is in the unlocked
position and the throttle is retarded to below 12 to 14
should be
in.
Hg.
of manifold pressure.
4
i.
2.
3.
4.
5.
6.
7.
6.
cover
THROTTLE WARNING HORN CAM
Rem ove the nut and bolt
Push in
wires and install the bolts
con-
together.
e.
appropriate
e.
f.
back to reveal the wire
nections.
d
the knurled knob and rotate the knob
and nuts.
REMO VAL
Push the wire
on
5
ENGINE
BOLT
NUT
PLATES (3 EACH)
ENGINE MOUNT
PLATES (5 EACH)
AN960-716L WASHER
AN960-716 WASHER
C95TH7180228 C
Figure
815
6-2.
Upper Engine
Vibration Isolator Mount
6-3
BARON 55 AN D 58
SHOP MAN UAL
THROTTLE WARNING HORN CAM
INSTA LL4 TION
Before the
if the
drilled, the th rottle butterfly valve should
NOTE
is new, the roll pin hole (.125- to .129-inch
will need to be drilled all the way th roug h.
The th rottle butterfly shaft may also need a matching
cam
hole drilled for the
roll
cam
pin.
a.
Place the th rottle
closed
position. (It
is
tion; consequently, it
closed
b.
valve
as
fully closed with the hig h lobe of the
straight up and lobe centerline
aligned with the cente rli ne of the throttle
body.
indid.
Place the
body butterfly valve in the fully
spring-loaded to the open posiwill have to be held in the fully
e.
high
cam on
the left side of the
Install the roll
and throttle
pin.
lobe of the cam
NOTE
butterfly shaft
Use two wraps of .032-inch safety wire
under the cam to
as shown. Refer
pointing up.
through the roll pin and
safety wi re the roll pin
to Figure 6-4.
The predrilled hole on a new cam should
be on the aft side of the cam to provide
better accessibility for drilling.
Push the
against
cam
f.
the throttle
linkage.
5
THROTTLE
IN
FULL
THROTTLE
Pig ure
Safety
wire the roll
pin.
g. Adjust the switch per TH ROTTLE WAR N I N G
HORN ADJ USTME NT in Section 5.
all the way onto the shaft until it
4
6-4
position, drill the
cam
shaft.
NOTE
butts
With the throttle still in the closed
1/8-inch hole (.125 to 129) in the
position.)
with the
c.
are
cam
If these holes need to
butterfly
and throttle shaft
be
diameter)
be drilled, position the cam and
cated. Refer to Figure 6-4.
cam
i.
2.
3.
4.
3.
MOUNTING BRACKET
THROTTLE BODY
SWITCH
CAM FOLLOWER
CAM
C95TH2780259 C
POSITION
6-3. Throttle
Warning
Horn Cam and Throttle
Body
El 5
~3eechcraft
BARON 55 AND 58
SHOP MAN UAL
OIL RADIA TOR REMOVAL
TC-I and after)
(Effectivity:
The oil radiator is located at the right front of each
engine. Removal may be accomplished as follows:
a.
Rem ove the
b.
Remove the 12
baffling
around the oil radiator.
mounting
Remove the radiator and
a.
Install
a new
gasket.
(Effectivity:
gasket.
b.
Install the radiator.
c.
Install the 1 2
mounting
bolts at the base of the
radiator
d.
b.
Disconnect the oil temperature bulb.
c.
Disconnect the oil drain line.
d.
Remove the five
e.
Remove the radiator and gasket.
baffling
retaining
nuts.
a´•
I nstal I
b.
Install the radiator.
c.
Install the five
d.
Connect the oil drain line.
e.
Con nect the oi I tem perature bulb.
f.
Install the
attaching bolts.
OIL RADIA TOR INS TALLA TION (Effectivity:
TE- I and after and TH- I and after)
OIL RADIA TOR INS TALLA TION
TC- I and affer)
I
Remove the 12
bolts at the base of the
radiator.
c.
a.
a n ew
Install the 12
g asket.
retaining
attaching
nuts.
bolts.
around the oil radiator.
OIL PRESSURE INDICA TOR
011 RADIA TOR REMOVAL (Effectivity:
TE- I and after and TH- I and after)
The oil radiator is located at the left
i ne. Rem oval m ay be accom pi is hed
rear
as
of each eng-
follows:
The oil pressure indicator was a direct-reading instrument on TH-1 thru TH-1395 except TH-1389. An elec-
trio oil pressure indicator was installed on TH-1389
and TH-1396 and after. The oil pressure transm itter is
located to the right of the engine centerline and is
attached to the aft side of the firewall
and rig ht engi nes.
2
3
on
both the left
OIL PRESSURE TRANSMITTER
REMOVAL (Effecfivity: TH- 1389 and
TH-1396 and after)
a.
Remove the stainless steel heat shield from the
engine nacelle.
bottom of the
NOTE
4
5
Note th e position of the electrical wi res
and label them for reinstallation.
THROTTLE IN IDLE POSITION
b.
Disconnect the electrical wires from the transm it-
ter.
I
2.
3.
4.
5.
SWITCH
CAM FOLLOWER
CAM
SAFETY W I RE
ROLL PIN
c.
Disconnect the oil line from the transmitter.
d.
Remove the screw
clam ped to the firewall.
e.
holding
the transmitter
Rem ove the transm itter.
C95TH27B0260 C
OIL PRESSURE TRANSMIT"TER
INS TA LLA TION
TH- 1396 and
a.
Figure
El 5
6-4. Throttle Warnl ng Horn Cam
(Effectivity:
after)
Place the transmitter in
install the
screw
TH- 1389 and
position
in the
clamp
and
in the clam p.
6-5
Ci~eechcraft
BARON 55 AND 58
S H OP MAN UAL
b.
Connect the oil line to the transmitter.
f.
c.
Connect the electrical wires to the transmitter.
valve.
d.
Start the
9´•
engine in accordance with the applicable
Operating Hand book and check for oil leaks.
Pilot’s
e.
Shut down the engine.
f.
Install the heat shield
on
the bottom of the
Connect the fuel supply line to the fuel manifold
I"stall the upper
(Effectivity:
Position the fuel line to the fuel manifold
valve before connecting the flexible blast
duct from the fuel metering valve.
engine
TC- 1 and
after)
AIR BOX REMO VAL
after and TH- I
a.
Remove the upper
b.
Disconnect the fuel
a.
Remove the upper
supply
ii ne to the fuel man if old
b.
Rem ove the fl exi ble duct from the air scoop duct.
c.
Remove the rod end from the
Disconnect the blast tubes to the generator or
alternator, fuelmetering valve, and the fuel pump at
the air box.
screws
engine baffle and the
securing
the air box to the
aft brace to the air box.
Remove the four nuts
metering valve assembly.
e.
f.
Disconnect the bracket
metering valve assem bly
mounting bolts.
attaching
on
the air box to the
the forward side of the
and
remove
angles (two)
d.
(Effectivity:
from the
Position the air box for installation,
b.
Install the
con nect
valve
assembly
mounting bolts.
e.box.LOOEen
valve
arm
the forward side of the
on
and
the flex duct
remove
the
and
clamp
angles (two)
remove
AIR BOX INS TALLA TION
and after and TH- I
(Effecfivity:
and after)
Install the air box to the flex duct and
b.
the air
Install the
on
the
mounting
the brace to the forward side of the
angles (two)
on
the
c.
tighten the
mounting bolts and
metering
assembly.
Install the rod end in the
flapper valve
arm assem-
bolts and
bly
metering
d.
Connect the flexible duct to the air scoop duct.
e.
Install the upper
assembly.
engine cowl.
NOTE
ENGINE CONTROLS ADJUS TMENT
On serials TC-1714 and after and prior
airplanes having complied with Service
Instructions No. 0688-258, tig hten the
four air box nuts only until a positive seal
is created between the throttle body and
the air box.
c.
Install the four nuts
metering
d.
valve
attaching
assembly.
I nstall the screws
securing
the air box to the air
the air box to the eng-
ine baffle and aft air box brace,
e.
Conn ect the blast tubes to the ge ne rater (or aiterfuel metering valve, and fuel pump at the air
TH ROTTLE AN D M IXTU R 8
TC-1 thru
TC-97)
On
airplanes
that are
equipped
with the
original
con-
trols, the following adjustment may be made to the
eng i ne th rottle
a.
or m ixtu re.
Remove the
glareshield to gain
t’01
assem
b.
Remove the two
c.
box.
the control
access to
the
con-
bly.
tion of the instrument
nator),
6-6
(Effectivlty:
screws
panel
securing
and tilt the
the upper porpanel aft.
Disconnect the control lever from the rod end
assembly adjustment
I
TE- 1
connect the brace on the forward side of the
valve
a.
valve
TC- 1
after)
angles (two)
flapper
clamp.
AIR BOX lNS TALLA TION
and
Disconnect the brace
metering
a.
Rem ove the ai r box,
cowl.
engine
assembly.
from
g.
TE- I and
cowl.
c.
Remove the
(Effectivity:
and after)
engine
valve.
d.
cowl.
N OTE
nacelle.
AIR BOX REMO VAL
engine
on
mechanism.
El 5
I
Qeechc~ft
BARON 55 AND 58
SHOP MAN UAL
d.
Loosen the locknut
bly adj usti ng
(upper)
on
the control
assem-
mechanism.
pull
upward
any tool
use
d~
cowl
the
position
openining is not 3.6
attaching bracket
setting.
ove rt i g hte n
against
the sleeve
required
the
n ut
this will increase
operate the control,
as
to
Turn the locknut down
g.
retaining
against
retaining
tightening the
locknut.
THRU TE-942 EXCEPT
I nstall the two
panel
and
replace
securing
glareshield.
screws
the
TH ROTTLE AN D MIXTURE
~C-98
(TE- 1
TE-938)
a.
Retract the cowl
b.
Disconnect the actuater shaft from the
c.
1
Adj ust
flap electrically.
d.
the instrument
the rod end
on
attaching
the actuator shaft to obtain
.1 inch of clearance between the
the cowl
Conn ect the control lever to the rod end.
h.
i.
inch, relo-
bracket.
the lower
nut. Do not let the rod end turn when
.1
to obtain th is
COWL FLAP ACTUA TOR RIGGING
NOTE
N eve r
flap should be
trailing edge of the
to the nacelle.
If the
retaining nut down against the
adjusting mechanism.
the effort
the act-
of the cowl
measured from the
cate the
Turn the lower
on
on
NOTE
the rod
exerting upward pressure
end; applying a strong pressure will
have a tendency to stretch the cable in
the control assem bly,
sleeve
flap
as
aid when
as an
on
f.
The extended
3.6-´•.1 inch
NOTE
Do not
Reinstall the 102933S92n660 spacer
uator shaft.
Hold the rod end to prevent its turning, then
on the rod end with a firm pressure.
e.
c.
flap
trailing edge
of
and the nacelle.
Connect the actuator shaft to the
attaching
bracket.
AN D AFTER,
TE-1 AN D AFTE R, TH-1 AN D AFTE R)
The
engine throttle and mixture controls may be
adjusted by loosening the jam nut, removing the rod
end pin, and turning the rod end either in or out to
obtain an adjustment which provides smooth operation of the controls. Refer to Figure 6-5.
CO WL FLA P A CTUA TOR RIGGING
THRU TC- 1607)
(TC- 1
This
right
rigging proced ure
flaps.
is
applicable
to both
and
left cowl
a.
Retract the cowl
b.
To
adj ust
flap electrically.
the actuator to obtain 1
clearance between the
trailing edge
.1 inch of
of the cowl
flap
and the nacelle, d isco n nect the actuator shaft at th e
attaching bracket, remove the 1 0293 3S92T1 6 80
100951S032XD
and
in stall
and
spacer
100951S063XD washers on the actuator shaft as necessary.
NOTE
Normally,
one
of each of the washers
on
the actuator shaft will be sufficient to
maintain the clearance
closed
615
flap position.
required
for the
Figure
6-5.
Eng ine
Controls
6-7
BARON 55 AND 58
SHOP MANUAL
The extended position of the cowl flap should be
e.
3.6 .1 inch as measured from the trailing edge of the
cowl flap to the nacelle.
3.
For TH1389 and TH-1396 and after the clearbetwee n the cowl flap and the cowling is .5 to
1.0 inch in the closed position and 4.4 to 4.6 inches in
ance
the open
NOTE
position.
f. Attach the pushrod to the cowl flap and check for
the desired clearance, making sure that the cowl
flap
control crank assem bly contacts the crank stop in both
If the open i ng is not 3.6
.1 inch, relocate the attaching bracket to obtain this
dimension.
the open and closed
COWL FLAP ACTUA TOR RIGGING
(Effectivity: TH- 1 thru TH-384)
Retract the cowl
a.
Disconnect the actuator shaft from the
bracket.
a
and the nacelle.
tendency for the cowl flap
fully closed position, rig the cowl flap bellcrank to an
on-center position or siig htly beyond.
h.
attaching
2. 6 ~.1 inch
cowl
flap
as
Loosen
or
position
of the cowl
measured from the
flap should be
trailing edge of the
tig hte n
on
the rod end to obtain a slight
the cowl flap controls in both the
open and closed positions.
i.
The extended
th e control cab le.
to creep away from the
cushion effect
bracket.
e.
n ut on
To reduce the
attaching
Adj ust the rod end on the actuator shaft to obtain
fitting between the trailing edge of the cowl flap
Con nect the actuator shaft to the
j am
NOTE
flush
d.
Loose n the
flap electrically.
b.
c.
g.
position.
Attach the control cable to the bellcrank
assem
bly.
j´•
Operate the cowl flap controls to both the open
positions, making sure that the clearance
for the cowl flap is correct, that the bellcrank assembly is contacting the crank stop in both positions and
that there is a slight cushion effect on the cowi flap
controls in each position.
and closed
to the nacelle.
NOTE
If the open i ng is not 2.6 ~t: .1 i nch, reloattaching bracket to obtain th is
dinension.
cate the
FUEL INJECTOR PUMP REMOVAL
MECHANICAL COWL FLAP RIGGING
a.
(Effectivity:
TC- 1 608 and after; TE-938,
TE-943 and after; TH-385 and after)
a.
Open
b.
Remove the attach bolt
the cowl
cable to the crank
c.
d.
the control
assembly,
connecting
the
pushrod
to
Loosen
jam
nuts at each end of the
pushrod.
on
tighten equally
pushrod to obtain the desired clearance for the cowl
flap as follows:
e.
or
the rod ends
the
1
For TO-i 608 and after and for TE-938,
TE-943 and after, the clearance for the cowl flap is 1 .O
in the closed position and 3.5 inches in the open position.
2.
For TH-385 thru TH-1 395
(except
TH-1
389),
the,cowl flap should be flush with the skin of the cowl-
ing
in he closed
in the
6-8
position
open position,
(See REMOVAL OF
after.) TE-I and after and
require removal of the air box.
and
THE
TH-1
b.
connecting
flap.
Loosen the
(TC-1
and after do not
flap.
Remove the attach bolt
the cowl
Remove the air box.
AIR BOX
and 2.5 inches from the skin
Disconnect fuel the lines, loosen the clam ps, and
the intake tube assem bly between the air
metering valve assembly and the No. 2 intake.
remove
Remove the lower
upper fitting from the
c.
fitting from the left side and the
right side of the fuel injection
pum P´•
d.
Remove the four screws from the injector pump
sh roud, discon nect the flexible d uct, and remove the
shroud.
e.
Remove the pum p
retaining
nuts and rem ove the
pum p.
FUEL INJECTOR PUMP INS TALLA TION
a’
b.
Place
a new
gasket
on
the pump
Place the pump in position
install the retaining nuts.
on
pad.
the
engine
and
515
’i~eechcraR
BARON 55 AND 58
SHOP MANUAL
Place the shroud in
c.
ing
screws
d.
position and
install the attach-
line of the p u m p. Adj ust the unmetered fuel pressure
psi at 625 to 650 rpm, then reset idle mixture to
best setting. This will produce a richer mixture at take-
and the flexible duct.
to 12
Install the upper fitting on the right side and the
fitting on the left side of the pump.
off and at fu II th rottle
lower
I nstall the intake tube assembly between the air
metering valve assembly and the No. 2 intake, then
e.
tighten
f.
the clam p.
Connect the fuel lines.
I nstall the air box if applicable. See INSTALLAg.
TION OF AIR BOX (TC-1 and after.)
Head the
airplane
PRESSURE ADJUS TMENT, ADJUSTABLE
ORIFICE FUEL PUMP, IO-470-L, IO-520-C
AND IO-520-CB ENGINES (Effectiviiy: 55,
A55, B55, 055, D55, E55, and 58)
Unmetered pressure can be checked by connecting test gage into the fuel pump outlet or from a fitting installed in the hex head of the filter screen
located at the bottom of the metering control unit.
a.
a
GROUND RUNNING AND WARM-UP
a.
operation.
into the wind.
b.
Operate the engines on the ground with the propeller blades set at the minimum angle thigh rpm) setting.
b.
Adjust engine idle speed to 625 to 650 rpm using
speed adj ustm ent o n the air th rottle with mixture control in the full rich position. Refer to Figure 6-6.
the id le
200" F and 460"F. Never allow the
perature to exceed 460"F.
Set the fuel pump relief valve adjustment, on the
C´•
ce"terline of the fuel pum p, to 9 to 1 1 psi by adi usting
the screw clockwise to raise the pressure and counter-
d.
clockwise to lower the pressure. Refer to
c.
Maintain the
cylinder head temperature between
cylinder head tem-
Extended
periods of idling
in fouled spark plugs.
at low rpm may resu it
d.
The Mixture controls should remain in the "FULL
e.
RICH" position unless leaning is required during the
checkout.
f.
Use
a
throttle
setting
of 1200 rpm for
engine
NOTE
back to id le. Move the mixture control to idle cutoff:
engine speed should increase approximately
25-50 rpm when the mixture control is moved toward
the lean position.
Advance the throttle to maximum rated engine
speed with the mixture control in the full rich position.
The unmetered fuel pressure should be 25 to 27.5 psi
investigate the
cause.
(IO-470-L Engines)
28 to 31
psi for 10-520-0
and
To increase the unmetered fuel pressure, turn the
recessed slot-headed needle valve (located just below
the fuel pump inlet fitting) in a clockwise direction, and
turn in a counterclockwise direction to reduce pressure.
FU EL SYSTEM ADJ U STM ENT
IDLE SPEED AND MIXTURE
NOTE
ADJUSTMENT, IO-470-L, 10-528-0
Any fuel system leaks may produce
erratic fuel system indications, and must
be fixed before proceeding.
IO-520-CB ENGINES
855)
can
rear
only
(Effecfivity: 55, A55,
855, C55, D55, E55 and 58)
PRESSURE ADJUSTMENT, FIXED
ORIFICE FUEL PUMP, IO-470-L (55 A55,
Fuel pressure on the fixed-orifice pump
by adj usti ng the screw located at the
or
f.
Normal oil
pressure at maximum rpm should be
30-60 psi and 10 psi at idie.
815
adjusting the idle unmetered pressure at 9 to
psi, check the idle mixture. Advance the throttle to
approximately 2,000 rpm to clear the engine, then
11
e.
An oil pressure indication of 10 psi
should be noted within 30 seconds in
warm weather. and within 60 seconds in
cold weather. If no pressure is noted
within the specified time, stop the engine
set
6-7.
the
warm up.
and
Figure
After
be
center-
Remove the side cowling and fairing
it from the left-hand side of the engine.
a.
directly aft
of
b.
I nstall an appropriate pressure gage in the fuel
line between the fuel pump and metering unit to monitor pump outlet pressures. This gage to be vented to
atmosphere.
6-9
I
’i~eechcraft
BARON 55 AND 58
SHOP MAN UAL
Start and warm-up the engine according
applicable Pilot’s Operating Handbook.
c.
to the
heating will occur even sooner with part
cowling removed. Monitor the cyl-
of the
and oil
tempera-
ture,
Retard the throttle to the idle
or
clockwise to increase the rpm,
cou nterclockwise to decrease rpm,
f.
position
to check the
adjustment,
Set the pump pressure at idle RPM (refer to Chart
the relief valve adjustment screw on the aft
centerline of the engine fuel pump. Refer to Figure
6-7. Turn the screw clockwise to increase
pressure
g.
6-1) using
and
position. Observe the rpm during
Tightening the nut to shorten the lin kage provides a richer mixture. A leaner mixture is
obtained by backing off the nut to len gth en the lin kage.
screw
Advance the throttle to 2,000 rpm then return it to
the idle speed
has been stabilized, move
a smooth steady pull into
throttle levers.
position.
e.
Adj ust the idle speed to 625 to 650 rpm with the
spring-loaded screw located forward of the air th rottle
lever. Turn the
setting
control lever with
Adjust the idle m ixture to obtain
approxim ately 25/50 rp m gain in the idle speed as th e
mixture control is slowly moved toward the IDLE CUTOFF. (If the mixture is too lean, the idle
speed will
drop under the same conditions.) The idle mixture
adjustment is the locknut at the metering valve end of
the linkage between the metering valve and the air
engine may overheat when operated on the ground for more than short
test periods. Exercise caution as over-
d.
cockpit
the lean ing process.
The
temperature
When the idle
the
the IDLE CUTOFF
NOTE
inder head
h.
co u nterclockwise
to decrease pressure.
i.
After each idle mixture
the
engine by running
ing
a
j.
If the idle
adjustment change, clear
it up to 2000 rpm before mak-
mixture check.
setting does not remain stable, check the
linkage; any looseness in this linkage will cause
erratic idling. In all cases, allowance should be made
for the effect of weather conditions
upon idling adjustidle
ments.
THROTTLE BODY
AIR THROTTLE LEVER
UP
,,,ct
STOP PIN
METERING UNIT
O
IDLE SPEED
ADJ UST MENT SORE W
IDLE MIXTURE
ADJUSTME NT N UT
VIEW OF LEFT SIDE OF THROTTLE BODY
AND METERING U NIT. (PLU MBING, I NDUCTION
AIR
SYSTEM, ETC. OMITTED FOR CLARITY.)
58-282-7
Figure
6-10
6-6. idle
Adjustment
El 5
~)eechcraft
BARON 55 AND 58
SHOP MAN UAL
NOTE
should be 625 to 650 rpm. If the engine is not
idling within the specified range, change the idle
speed adjustment screw as required to obtain the
proper idle speed. Refer to Figure 6-6. Turn the idle
speed adj ustment screw clockwise to increase rpm
speed
After each idle mixture adjustment, clear
the engine by increasing rpm to approximately 2000 before making the next mix-
and
IDLE SPEED AND MIXTURE
A DJUS TMENT (Effectivity: TH- 1389,
TH- 1396 and after IO-550-C
Install
Engine)
run
engine according th the warm-up
applicable Pilot’s Operating Hand-
625-650
*2625
10-520-BE
625-650
and
FUEL FLOW
LBSIHR
GALIHR
I
1
I
are
obtained
1
UNMETERED OR PUMP
OUTLET PRESSURE
I
1
20.5- 21.7
1
16.5
136- 146
I
1
22.7- 24.3
I
17.9-18.5
(851)
(R E F. ON L
9-11
25-27.5
1
15.5
achieved with full throttle,
values
(APPROX.)
I
123-130
9-11
28
1
8.00
31
10.00
35-38
Valu es g iven are for maximum rated RPM. If
rated rp m at static ru n-up can not be
given.
I
15.5-16.5
*2700
below values
an idle mixture adjustrequired, turn the idle mixture adjusment nut
as necessary eig hte n the nut to enrich the mixture or
loosen the n ut to lean the m ixtu re) to obtain the correct idle m ixtu re. Refer to Figu re 6-6.
FUEL FLOW
625-650 1
IO-550-C
lean, the rpm willdrop. If
METERED OR
’2700
IO-520-CB
idle rpm and the fuel pump
the mixture to attain a momentary
specified
NOZZLE PRESSURE
PSI
IO-470-L
Adjust
ment is
the
RPM
Maintain the
pressure.
too
book. Move the mixture control to fu I I rich. The idle
ENGINE
d.
of 25 to 50 rpm when the mixture contro I is
moved toward the idle cutoff position. If the m ixtu re is
The pressure gage should be vented to
the atm osphere.
i n the
achieve the proper pump pressure, turn the relief
adjustment screw clockwise to increase pressure and c’ounterclockwise to decrease pressure.
Refer to Fig ure 6-7
gain
NOTE
Start and
engine-driven fuel pump pressure should
psig. If adj ustment is required to
valve
a
proced u res
adjust flow slightly
specified
Make certain
I
"X
When
setting up fu II throttle fuel flow on an above standard
day (above 60 "F), the system should be set toward the
lower limit. On a below standard day (below 60"F), the system should be set toward the hig her fl ow I imit.
achieved when rated rpm is
takeoff roll.
during
BT04878
Fuel Pressure and Flow
Chart 6-1
El 5
I
to decrease rpm.
read 8.00 to 1 0. 00
gage will be used to monitor fuel pump outlet pressure
(also called unmetered pressure).
b.
The
c.
pressure gage in the fuel line between the
engine-driven fuel pump and the metering unit. The
a.
cou nterclockwise
6-11
I
Ci3eechcraft
BARON 55 AND 58
SHOP MAN UAL
NOTE
Afte r each mixture
adj ustm ent, clear th e
engine by running up to approximately
2000 rpm before making the next mix-
position in order to provide the most accurate reading.) Return the fuel from the Flow Rater back to the
airplane fuel system through the wing filler port.
NOTE
ture check.
Use
external power supply capable of
28.25
.25 volts for the source
of electrical powe r.
(Effectivity:
Install
a.
engine
TN- 1389, TH- 1396 and
after)
pressure gage in the line between the
fuel flow transducer and the manifold valve.
a
c.
Tu rn the
d.
Adj ust
to the test
plane
The pressure gage should be vented to
the atm osphere and m ounted at approxi
mately the same level as the manifold
valve.
Run the
engine
until normal
operating
the Flow Rater
readings
fuel flow
(gph)
(using
the
adjustable valve)
in Chart 6-3 and record the airfrom the fuel flow indicator
on a
The throttle and mixture levers must be
forward. Use the adjustable valve
shown to adj ust the fuel flow as necessary. Refer to Fig ure 6-8.
fully
tem perae.
With the mixture control in the fu II rich
position,
advance the th rottle control to fu II throttle and maximum
AUX FU EL PUMP to HI.
NOTE
tures are attained.
c.
airplane
copy of Chart 6-3.
NOTE
b.
an
providing
FULL THRO TTLE FUEL PRESSURE
ADJUS TMENT, 1C-550- C ENGINE
static rpm. Check the metered fuel pressure.
Once
an error
in the
airplane
fuel flow hardware
has been determined. Correct the system
following
exam
as
in the
pie:
EXAMPLE:
d.
Refer to Chart 6-2 to determine of the correct
metered fuel pressure. If a fuel pressure adjustment is
req uired, tu rn the fuel bypass adjustment screw as
necessary to obtain the correct metered fuel pressure.
Turn the
bypass adjustment
increase pressure
pressure. Refer to
or
screw
clockwise to
counterclockwise to decrease
Figure
6-7.
At 80
pph flow rate with the fuel temperature at 40" F,
airplane fuel flow indicator reads 13.0 gph. Using a
fuel density of 5.9, Chart 6-3 shows the indicator
should be reading 13.5 gph. Therefor, the instrument
error is 0.5 gph low. When the airplane indicator is
reading 13.0 gph, add 0.5 gph for system correction.
an
NOTE
NOTE
This fuel flow indicator check should be
made at all ten flow rates as the system
error may vary as the flow rate changes.
The fuel pump
a
adjustment proced u re is
starting point for fuel pressure adj ust-
ment at full throttle. "FUEL FLOW SYSTEM CALIBRATION AND CORR ECTION" MUST also be com pleted.
FUEL FLO W S YS TEM CALISR4 TION AND
CORRECTION (Effectivify: TH- 1389,
TH- 1396 and
after)
(Figure 6-8)
A fuel flow system calibration and correction should be
obtained from the following procedure:
a.
Rem eve the uppe r eng i ne
b.
Install
a
flow meter at
and the
cowling
bly.
Fisher Porter Flow Rater or equivalent
a point between the fuel flow transducer
engine
fuel distributor valve.
ter Flow Rater must be instal led in
6-12
assem
(The Fisher Pora straig ht vertical
f.
Repeat the preceding steps
for the
opposite eng-
ine fuel flow system.
NOTE
The FU LL TH ROTTLE FU EL PR ESSURE ADJUSTMENT,
IO-550-C
TH-1389 and TH-1396 and after) procedure M UST be com pleted before pro-
ceeding.
g. Flight check for proper engine fuel schedule.
Establish a climb at 110 kias (knots indicated air
speed).
Th rottle
Prop
Fu I ly Forward
.2500
515
~edzcraft
BARON 55 AND 58
SHOP MAN UAL
NGINE DRIVEN FUEL PUMP
ELIEF VALVE ADJUSTMENT
(USED TO SET
PUMP PRESSURE)
SCREW
IDLE
UP
aD
FWD
VARIABLE ORIFICE ADJUSTING SCR EW
(USED TO SET FUL’L THROTTLE PUMP
PRESSURE)
VIEW OF LEFT SIDE OF ENGINE DRIVEN FUEL PUMP
TYPICAL FOR THE 10-52088 ENGINES
(FITTINGS, COOLING SHROUD, ETC. OMITTED FOR CLARITY)
36-283-2
IO´•410L WITH ADJUSTABLE ORIFICE PUMP, IO-520C AND IO´•520CB ENGINES
RELIEF VALVE ADJUSTMENT ~CPFW
(USED TO SET PUMP IDLE ssESSUSE!
ANEROID ADJUSTMENT SCREW
(DO NOT TURN)
UP
FWD
JAM NUT
ENGINE DRIVEN
FUEL PUMP
BYPASS ADJ USTMENT SCREW
(USED TO SET FULL THROTTLE
PUMP FLOW) (5/32 ALLEN SCREW)
VIEW OF LEFT SIDE OF ENGINE DRIVEN
FUEL PUMP. (FITTINGS, COOLING
SHROUD, ETC. OMI1TED FOR CLARITY)
IO-550-C ENGINE
Figure
516
6-7. Fuel
Pump Adjustment
6-13
~)eed´•lcraft
BARON 55 AND 58
S H OP MAN UAL
M ixt ure
Boost
h.
Fu I I Rich
Pump
Off
Record the fuel flow at all pressure altitudes
set at 29.29 in. Hg.) shown in Chart 6-4 if
(altimeter
possible.
i. Wh ile i n flig ht at 8,000 feet, set power to 20.5 in.
manifold pressure with the prop at 2,300 rpm and mixture control at full rich. The EGT margin should be 20"
C to the rich side of peak temperature or greater. Next
lean the mixture from peak to eng ine rough ness. The
margin
should be 20" C to the lean side of
perature
or
peak
te m
greater.
Foreign
m atter
result in
a
lodg ed between the ball and seat
drop in oil pressure. It is advisable to disassemble, inspect, and clean the relief valve if excessive
pressure fluctuations
If the fuel flow at 12,000 to 16,000 feet is
below the minimum required in Chart 6-4
for high altitude, check and reset the idle
unmetered or pum p outlet pressure to
the upper limit. Refer to Chart 6-1, 8.0010.00 psi.
j.
If the corrected fuel flow does not fall within the
req uired fuel flow I im its (see Chart 6-4) or if the rich
side-of-peak margin
noted.
HIGH OIL TEMPERA TURE
Oil tem perature is controlled by a spring-loaded oil
cooler valve. This valve will operate properly if the oil
has not become contaminated with dirt or other foreign particles. If indications are that the valve is not
operating properly, remove the valve and clean it in
solvent (Item 1 5, Consumable Materials Chart, Section 2). Also inspect the valve seat for damage. No
repairs
NOTE
are
be made to the valve and
adjustments are
special testing eq uipment is
required. The travel of the valve can be checked by
immersing the valve assembly in heated water. The
can
not recom mended since
minimum amount of travel should be 0.090 inch
tem peratu re is raised from 1 20" F to 1 700 F.
as
the
Replace
defective valves.
MAG N ETOS
RPM DROP- OFF CHECK
is not obtained, readjust the
metered eng i ne fuel press u re refer to step d of FULL
TH ROTTL E F U E L P R ESS U R E A DJ U STM E NT,
The purpose of the drop-off check is to determine that
the electrical system for firing the fuel in the cylinders
IO-550-C
of the
Engine (TH-1 389
and TH-1 396 and
after).
bypass adjustment
screw clockwise to increase pressure (fuel flow) or
counterclockwise to decrease pressure (fuel flow).
Refer to Fig ure 6-7. One psi is approximately eq ual to
one gph.
Turn the
engine-driven
fuel pump
NOTE
engine is in a satisfactory co nd ition. A drop in
rpm is a natural characteristic while operating on
sing le i g n ition of a dual ignition system. The abse nce
of an rpm drop may be an ind ication of the magneto
timing advanced beyond the setting specified, or of an
open magneto primary lead (hot mag), or of a defective mag switch. Verify the cause before checking mag
timing.
Conditions: Full Throttle, Full Rich,
Boost Pumps off, 2500 rpm, 110 kias.
CAUTION
Never advance the timing beyond the
specifications in order to reduce rpm
drop. Timing advanced beyond the setting specified by the engine manufacturer can cause detonation and/or preignition, resulting in broken rings, cracked
and burned pistons and abnormal and
excessive stress induced into cylinder
heads, cylinder barrels, crankcase,
crankshaft and connecting rods.
OIL PRESSURE ADJUS TMENT
The fu nction of the oil pressure relief valve is to mainengine oil pressure within specified limits by withdrawing a portion of the oil from the circulating system
and returning the oil to the sump.
tain
The oil pressure adjustment screw is located approximately 3 inches below the oil filter housing. To adjust,
turn the
adjusting screw clockwise to increase, or
counterclockwise to decrease, the oil pressure. The oil
pressure should be 10 psi minimum at idle and
between 30 to 60 psi at maximum operating rpm and
The
tem peratu re.
lows:
6-14
drop-off
check should be
accom
pi is hed
as
fol-
El 5
aeechcraft
BARO N 55 AN D 58
SHOP MAN UAL
OPERATING CONDITIONS
Full Throttle, Static R. P. M., Full Rich
20.0 43~
´•i
"C"
i´•´•~-´•1
re;
~ti
i´•´•~1
i:
i
I
i
i
´•´•1
´•$´•´•´•i:
ii
k´•´•"´•´•-I´•´•´•´•´•´•’
"B"
c´•´•l´•´•´•´•´•´•´•
´•´•´•´•I
i-´•s´•´•~
~´•´•i
~´•i
C´•i
1´•´•´•i´•-~
i
i
C-i
i
i
I
r,i´•´•´•-´•~
r
18.0
;-j,´•-;´•a
i´•´•´•~´•i t´•´•~
~´•´•t
~´•t´•i´•
tl´•l
c~
n
i
i i´•´•1
19.0
~3
i
i´•´•~´•´•i
i´•Il´•i
I
i
i´•´•--"
1
1
d´•:
´•I
W[r
V>
V)
i
17.0
i´•~´•´•i
c´•i´•´•´•
w
a:
t´•?
e
w
F.."..’.;o
16.0~i
´•´•´•´•´•´•(´•´•1
3
u.
o
w
a
cr:15.0
w
~´•-´•´•´•i
i-i
w
w
i
r
´•1-´•-´•´•´•´•´•´•-´•-~´•"´•´•´•´•´•´•’´•´•´•´•
C´•´•’:
14.0
i´•´•i
i´•´•i
c´•:i´•´•´•!
i
i-´•i
i´•J
Ei~i
i´•´•´•~
t
t
´•i-´•
c´•?
I´•-i
13.0
22.0
23.0
i
SET M ETE RE D P R ESS U RE TO
.3 PSIG
VALU E SHOWN
1´•´•´•1´•´•´•´•´•´•1´•´•´•´•-´•´•´•´•":´• I´•´•´•r-´•´•’´•´•´•1´•~
i
i
C´•´•´•l´•-
c´•~´•´•i
24.0
"A"
25.0
26.0
MANI FOLD PR ESS U R E
29.0
28.0
27.0
(IN. HG.)
58-282-8
LOCATE MANIFOLD PRESSURE ATTAINED DURING FULL THROTTLE STATIC RPM RUN-UP
(POINT ’’A’’).
AT THE POINT WHERE THE MANIFOLD PRESSURE READING INTERSECTS THE NOMINAL METERED
PRESSURE LINE (POINT "B"), READ THE METERED FUEL PRESSURE IN PSIG (POINT ’’C’’). FULL THROTTLE
METERED FUEL PRESSURE IS TO BE SET AT THE INDICATED VALUE
.3 PSIG.
NOTE: THIS IS A SAMPLE; VALUES SHOWN MAY VARY FROM UNIT TO UNIT.
Full Throttle Fuel Pressure Chart For The IC-550-C
Engines
Chart 6-2
515
6-15
~eechnaft
BARON 55 AND 58
SHOP MAN UAL
ENGINE FUEL FLOW
TRANSDUCER
ENGINE DISTRIBUTOR
VALVE AND NOZZLES
AIRP LANE FU EL
FILLER PORT
FLOW RATOR
(MUST
BE IN A STRAIGHT
VERTICAL
POSITION)
ADJ U STABLE VALVE
AIRPLANE WING
936-281-43
Figure
6-16
6-8. Fuel Flow CalTbratlon
E15
~echcraft
BARON 55 AND 58
SHOP MAN UAL
TEM PERATU RE WHEN FUEL FLOW IS CH ECKED (FU EL TEMPE RATU
RE)
Flow Rater
Setting
in Pounds
Per Hour
(pph)
Flow Of Fuel In Gallons
Per Hour (gph) Based on
Density (Tem peratu re)
Ibs.per.gal.
6.0
5.9
5.8
5.7
gph
gph
gph
gph
gph
Flow 60 pph
10.0
10.2
10. 3
10.5
gph
gph
gph
gph
Flow 80
pph
13.3
13.5
13.8
14.0
gph
gph
gph
gph
Flow 90
pph
15.0
1 15.3
15.5
15.8
gph
gph
gph
gph
Flow 110
pph
18.3
18.6
19.0
19.3
gph
gph
gph
gph
Flow 120
pph
20.0
20.3
20.7
21.0
gph
I gph
gph
gph
Flow 140
pph
23.3
23.7
24.1
24.5
gph
gph
gph
gph
Flow 160
pph
26.7
1 27.1
27.6
28.0
gph
gph
gph
gph
Flow 180
pph
30.0
30.5
31.0
31.5
gph
gph
gph
gph
Flow 200
pph
33.3
33.9
34.5
35.0
gph
gph
gph
gph
Flow 210
pph
35.0
35.5
36.2
36.8
Density
On
Of Fuel Based
Temperature
Record Airplane
Correction To
Fuel Flow From
Airplane Fuel
Flow System (gp h)
I n dicator
Density
(9 ph)
L.H.
R.H.
(13. 0 gph
in example) I
20"F..........6.0 ibs. per. gal.
140"F
D EGRE ES F.
.........5.9 ibs. per.
gal.
0.5 gph
example)
170"F
I
L.H.
100"F
...................5.8
.................5.7
R.H.
in
ibs. per.
ibs. per
gal.
gal.
BT04877
Fuel Flow Check
Chart 6-3
E15
6-17
BARON 55 AN D 58
SHOP MANUAL
Start and operate the
a.
engine at full rich mixture,
pitch at 1,200 rpm until a normal
tem peratu re (200" to 460" Fl has been
BENDIX MA GNETO TIMING
with the prop in low
warm u p
To determine if the
obtained.
ceed in the
b.
Advance the throttle to obtain 1,700 rpm.
Move the magneto switch to the R
observe the rpm drop.
d.
a.
position
c.
and
C´•
plugs.
f,
position
Secu’e
a
secure a
spark plug
properly
tim ed, pro-
from each
cylinder.
pointer on the nose case of the engine
timingdisc to the propeller shaft.
NOTE
and
If
a timing disc
pellar may be
is not available the proremoved and the timing
marks inscribed on the crankshaft flange
Move the magneto switch to BOTH and clear the
plugs.
d.
Turn the crankshaft to find the top dead center of
one cylinder on the com pression stroke.
the
zero
Align
degree mark on the timing diso with the
Shut down the engine to idle then off,
g.
following
Remove the top
are
manner:
Install any suitable top dead center indicator in the
spark plug port of the num ber one cylinder.
and
Move the magneto switch to the L
observe the rpm drop.
magnetos
b.
Move the mag neto switch to BOTH and clear the
e.
(5-200
SERIES)
the number
NOTE
pointer.
Maximum drop for either magneto and
the difference between the two magnetos should conform to that noted in the
the crankshaft
applicable
20" ETC.
Conditions:
Pilot’s
Operating
e.
Connect
mal rotation.
Handbook.
Engine instruments-ships indicators, Full throttle,
timing light to the left magneto and turn
approximately 28" opposite to the norThe timing light should come on at about
a
Full rich,
Boostpumps off,
2500 rpm, 110
kiss.
Pressure Altitude
Obsenred Fuel
(5et Alitmeter At
29.92 in. Hg)
Static
F low I n
L.H.
Flight
R.H.
System Correction
Corrected Fuel
From C ha rt 3
Flow
L.H.
R.H.
L.H.
Required
(9 ph)
Fu e I F low
R.H.
Run-Up
2,000
4,000
1
1
6,000
8,000
10,000
12,000
14,000
16,000
1
I
1
1
1
I
1
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
I
i
I
1
1
1
I
I
1
I
1
122.2 to 24.6
120.7 to 22.5
119.2 to21.3
1 17.8 to 20.6
1 16.4 to18.9
115.0 to 17~8
1 13.6 to 16.8
112.3 to 15.9
BT04876
Altitude Versus Fuel Flow
Chart 6-4
6-18
El 5
C~eechcraft
BARON 55 AND 58
S HOP MAN UAL
NOTE
When
timing
the magnetos
serials TC-2 thru
the
BENDIX MAGNETO TIMING
TC-23, do
not rotate
Check the magneto for proper rotation before
replacing the m ag neto on the engine.
a.
propeller
shaft op pos ite t h e normal
d i rect i o n of rotat io n far e n o u g h to
engage the mag neto i m pulse drives.
This will delay the opening of the points
until the
piston
inpulse drives
is at
top
center.
do become
b.
Remove the timing inspection plug from the top of
the magneto, and turn the magneto drive shaft in the
direction of rotation until the timing mark on the distributer gear is approximately aligned with the mark on
the distributor block. The magneto is now in the No. 1
cyl i nd er fi ri ng position.
If the
engaged,
rotate the shaft in the no rm al d i rectio n
until the points open, then in the oppo-
site direction for
(S- 1200
SERIES)
airplane
on
approximately
28".
NOTE
f.
Turn the crankshaft in the normal di rection of rotation until the light just goes out and note the degree
2"
The timing marks are for reference only.
No adj ustment of contact opening shall
be made from these marks. Use these
timing light to the right magneto and
ai
turn
the
n
crankshaft
ag
approximately 28" opposite
the normal rotation. The timing light will come on at
indication of proper i nternal
of the magnetos refer to Bendix, Scintilla Division,
manual Form L-609B.
before TDC. The
before TDC.
light should go
out at 20"
0"
marks
Connect the
g.
about 20" ETC.
h.
Turn the crankshaft in the normal direction of rotation until the light just goes out and note the degree
before TDC. The
light
should go out at 20"
0"
2"
before TDC.
Position the engine piston in No. 1 cylinder (right
cylinder) to fully advanced position by covering
the lower spark plug hole in No. 1 cylinder with the
C’
rear
thumb and
If the
preceding proced u re is used and the magnetos
2", they are timed correctly. If the
magnetos are not timed correctly, proceed in the following manner:
1.
on
Set the
the
num ber one
compression
piston
at 20" before TDC
Loosen the
3.
Rotate the magneto until the
light just goes
4.
Tighten
the magneto
nuts.
5.
Repeat
the
right magneto mounting
mounting
procedure
for the left mag-
neto.
the alternator drive gear as the crankshaft is
slowly. When the mark on the gear is centered
in the viewing hole, No.l piston is at the 20" ETC
e.
safety
f.
Breaker points on Bendix Scintilla
S6RN-25 type magnetos are not to be
adjusted to a given clearance. For
proper S6RN-25 mag neto adj ustm ent,
refer to Sci nti I I a’s i nstruct ions.
515
engines
and 22" ETC
position
engines.
on
the
engine an d tig hten
permit rotating
to
the
the
Con nect the positive lead of
a timing light to the
(capacitor stud) of the magneto and
ground lead to a suitable ground.
switch terminal
the
NOTE
When
the
wire,
NOTE
the 10-470
I nstall the magneto
secure
screws, and secure with
on
the 10-520
mounting bolts only enough
magneto for final timing.
After magnetos have been properly tim ed, clean the
breaker points to remove any trace of oil or dirt.
Replace the breaker cover, lock washers and retain-
ing
Remove the threaded plug in front of No.6 cylinfront cylinder) and observe the timing marks
(left
rotated
nuts.
out.
the crankshaft until pressure is felt
on
on
2.
same
d.
der
position
stroke.
turning
the thumb.
on
check within +0"
as an
timing. For internal timing
timing the magneto to the engine,
timing light should go out 20"+ 0"
2" ETC.
If the timing light is out, rotate the magneto housing in the direction of its magnet’s rotation a few
degrees beyond the point where the light comes on,
then slowly tu m the mag n etc in the opposite direction
until the light just goes out. Secure the mag netc in this
position an d rech eck the adjustment.
g.
6-19
Qeechcraft
BARON 55 AND 58
SHOP MANUAL
h.
Disconnect the
make
con nections
timing light
from the magneto and
to the mag neto’s switch and retard
terminals.
Bendix
Timing
Kit No. no. 11-8150-1 is available for
m ag neto. S I ick T1 00 Assembly
i nter nal ti m i n g of the
and
Timing
Kit is available for Slick magnetos.
NOTE
WARNING
For
The magneto is in a SWITCH ON conditlon when the switch wire is disconnected Disconnect the switch wire at
the capacitor and ground the capacitor to
nect the outlet
neto
I
i.
Check magneto contact assemblies as
Section 16. Points with deep pits or with
burned
points
areas
can
specified in
excessively
should be discarded. If necessary,
by using any hard finished
be cleaned
paper. I nspect the felt of the cam follower for proper
lubrication and clean the breaker com partment with a
dry
cloth.
It is assumed that the magnetos have been internally
timed properly with the points adjusted pe r th e appli-
cable Bendix
or
Slick vendor
magneto points other than
publication. To adjust the
specified in the appli-
as
cable vendor
publication manual will alter the magneto
"E" gap and cause a weak spark. This internal timing
and point adj ustment shou id not be made on the airplane.
opening
and
On Bendix magnetos, turn the magneto drive in the
opposite to normal rotation (this keeps the
impulse couplers from engag ing; nonim pu ise coupled
magnetos may also be rotated opposite to normal
direction
rotation)
until the respective
th roug h the i nspection
For
inspection purposes, the point gap may be
cam follower is resting on the high
the cam robe. The magneto point gap should
timing
mark
(viewed
the distri butor gear is
hole)
aligned with the divided casting line of the magneto
housing. Now the mag neto is ready to install on the
engine and
MAGNETO POINT GA P AND TIMING
I
of contact
PREPARING THE BENDIX MA GNETO
FOR INS TALLA TION ON THE ENGINE
suitable
ground, or disconplate from the magor spark plug leads.
a
adjustment
internal timing of Bendix or Slick magnetos, refer to the applicable vendor manuals. Check magneto contact assem bl ies
as specified in Section 16.
is
ready
on
to fire the num ber 1
cylinder.
PREPARING THE SLICK MA GNETO FOR
INS TALLA 7/ON ON THE ENGINE
Insert the T-l 18 tim ing pin (or
a.
the R hole in the distributor block.
a
sixpen ny nai I)
in
b.
Turn the magneto drive in the direction opposite to
normal rotation until the pin inserts through the hole in
the gear (approximately 1/4 inch).
checked when the
poi nt of
be
as
NOTE
follows:
MAGNETO.......................POINT
If the pin is binding, but will not insert
into the hole in the gear, it has hit the
pointer on the gear. Pull the pin out until
the pointer has passed, reinstall the pin
and conti n ue rotation until the pi n inserts
in the hole in the gear.
GAP IN INCHES
Bendix SGRN-1201
Main Breaker...,..,..
....................0.01
Retard Breaker
6
0.003
0.016
0.006
c.
Bendix 86 RN-1 205
and
Breaker..........................................0.01
6
0.003
Bend ix 86 R N-l 225
Main Breaker................................O.01
6
rt
6-20
ready to
to
install
d,
the engine
cylinder.
on
num ber one
As soon as the m agneto is i nstal led
ine, the timing pin MUST be removed.
on
the eng-
CAUTION
Main Breaker
..............0.009
magneto’s internal timing
should be made at
now
supply ignition spark
0.003
Slick 6210
The
The magneto is
and
0.001
point adjustment
the time of assem bly or overhaul.
If the magneto drive is rotated with the
the magneto will be
timing pin installed,
damaged.
515
I
~eechcraft
BARON 55 AND 58
S HOP MAN UAL
REMOVAL OF THE MA GNETOS
f.
Remove the four
a.
outlet and
remove
screws retaining the high tension
the outlet from the magneto.
Connect the timing light lead to the ground terminal of each magneto. Both timing lights should be on.
Tap the rig ht magneto up with a nonmarring hammer
until that
until the
CAUTION
Remove the
grounding
wire from the magneto.
Remove the two magneto retaining nuts and
washers and pull the magneto away from the accesc.
sory
down
g. Turn the crankshaft a few degrees counterclockwise and bring it back again until the timing marks are
Current production magnetos do not
have the automatic grounding devices
featured on earlier Scintilla magnetos,
To be safe, treat all magnetos as hot
whenever the ground lead is disconnected. To ground the magneto, connect
a wire to the switch lead of the magneto
and ground the wire to the case.
b.
light goes out. Tap the left magneto
light goes out. Secure the magnetos.
case.
aligned.
At this
point
both
timing lights should go out
timing mark on the crankcrankcase parting flange or
at the same instant that the
shaft
flange aligns with
the ti m ing mark
the
the alternator drive gear appears in
the center of the crankcase inspection hole.
on
h. If the timing lights do not go out at the same time,
loosen the magneto that is late or early and repeat the
process outlined in steps e and f.
INS TA LLA TION AND TIMING OF SLICK
MAGNETOS
(10-470 ENGINES)
To determine if the
m ag netos are
properly timed, pro-
INS TALLA TION AND TIMING OF
ceed in the
MAGNETOS (10-520-0, 10-520- CB A ND
10-550-0 ENGINES)
Cover the lower spark plug hole of No.l cylinder
a.
with thumb and turn the crankshaft until pressure is
felt on thumb.
Remove the lower spark
a.
plug
from each
cylinder,
Cover the lower spark plug hole of No. 1 cylinder
with th um b and turn the cran kshaft until pressure is
b.
felt
on
th u m b.
Remove the plug in front of No. 6 cylinder and
c.
observe the ti m ing mark on the alternator drive gear
as the crankshaft is rotated slowly. When the mark on
the gear is centered in the viewing hole, No. 1 piston
is at the 22"
i" ETC
position.
Prepare the magneto for installation on
engine as described in PREPARING
the
THE MAG N ETO FOR INSTALLATION
ON THE ENGINE.
d.
Hold the magneto in the position it will occupy
when installed, and check alignment of gear coupling
slot and impulse coupling lugs. If not aligned, pull the
gear out of mesh but not out of the oil seal. Turn to
correct alig n ment and push the gear back into mesh.
Place a new gasket on the magneto flange, and
install the magneto carefully so that the drive coupling
lugs mate with the slots of the drive coupling. I nstall
holding was hers, lock washers and nuts, b ut tighten
e.
looseness)
El 5
to perm it tu ming the magneto
for final timing.
manner:
U,,
timing disc or marks on the crankshaft
engine crankcase parting surface or marks
on the generator/alternator drive pulley to position
No.l piston at the 20"
0" 2" ETC position.
flange
c.
and
Remove the
inspection
hole
plugs
from the mag-
netos.
NOTE
The red
NOTE
only enough
b~
following
(without
timing marks, located on the
side of the magneto with the tradem ark,
should be in line at 20"
0" 2" before
TDC. When the red marks are in line,
the black marks visible through the vent
hole
on
the
opposite
side
are
in line.
d. Turn the im pu ise coupling backward, so latches
will not engage until the timing pointer inside the
inspection hole is aligned with the marked distributor
gear tooth.
Insert the timing pin through the hole in the frame
e.
and rotor shaft. Th is holds the magneto for tim ing to
the engine. Hold the magneto in the position it will
occupy when installed, and check the alignment of
gear coupling slot and impulse coupling I ugs. If not
aligned, pull the gear out of mesh, but not out of the
oil seal, and turn to correct align ment. Push the gear
back into mesh.
6-21
’i3eechcraft
BARON 55 AN D 58
SHOP MAN UAL
f.
Place a new gasket on the magneto flange and
install the magneto carefully so drive coupling lugs
mate with the slots of the drive bushings. Install holding washers, lock washers and nuts, but tig hten only
enough
ness)
to perm it turn ing the magneto
for final timing.
(with o ut
light goes
out. Secure the
magnetos.
Insert the timing pin through the hole in the frame
and rotor shaft. This holds the magneto for timing to
the engine. Hold the magneto in the position it will
occupy when installed, and check the alignment of
e.
Rotate the crankshaft until the impulse
clicks, then rotate the crankshaft opposite the normal direction of rotation to
the approxi m ate 25" ETC positio n. Care
m ust be exercised to be su re the crank-
gear coupling slot and im pulse coupling I u gs. If not
alig ned, pull the gear out of mesh, but not out of the
oil seal, and turn to correct alignm ent. Push the gear
shaft is not turned to the point where the
magneto im pulse drives are engaged;
h.
Turn the crankshaft
wise and
aligned.
bring
it back
a
will be
few
again
d. Turn the im pulse coupling backward, so latches
will not engage, until the timing pointer inside the
inspection hole is aligned with the marked distributor
gear tooth.
NOTE
opening of the points
approximately 26".
The red timing marks, located on the
side of the magneto with the trademark,
should be in line at 220
0"
2" ETC.
When the red marks are in line, the
black marks visible through the vent hole
on the opposite side are in line.
loose-
g. Connect the timing light lead to the g ro u n d term inal of each magneto. Both timing lights should be on.
Tap the right magneto up with a nonmarring hammer
until that light goes out. Tap the left magneto down
until the
NOTE
back into mesh.
delayed by
f.
degrees
u ntil
counterclockthe tim i ng marks are
At this
point both timing lights should go out
at the same instant that the timing mark on the crankshaft flange aligns with the crankcase parting surface
or the timing mark on the generator/alternator drive
pulley aligns with the 20" 0" 2" timing mark,
i.
If th e timing lights do not go out sim u itan eously,
loosen the magneto that is late or early and re peat th e
process outlined in steps g and h.
Place a new gasket on the magneto flange, an d
install the magneto carefuny so that the drive coupling
lugs mate with the slots of the drive bushings. Install
holding washers, lock washers and nuts, b ut tig hte n
only enough to perm it turning the magneto (without
looseness) for final timing. Remove the timing pin.
g. Connect the timing light lead to the g rou nd term inai of each magneto. Both timing lights should be on.
Tap the right magneto up with a nonmarring hammer
u ntil
that
u ntil
the
light goes out. Tap the left magneto
light goes out. Secu re th e magnetos.
down
NOTE
INS TALLA TION AND TIMING OF SLICK
MAGNETOS (10-520 AND /0-550
Rotate the crankshaft until the im pulse
clicks, then rotate the crankshaft oppo-
ENGINES)
To determine if the magnetos
ceed in the following manner:
are
properly timed,
site the normal direction of rotation to
approximately the 25" ETC position.
Care must be exercised to be sure the
cran kshaft is not turned to the point
where the magneto impulse drives are
pro-
Cover the lower spark plug hole of No. 1 cylinder
a.
with thumb and turn the crankshaft until pressure is
felt on thum b.
b.
Remove the plug in front of No. 6 cylinder and
observe the timing mark on the alternator drive gear
as the crankshaft is rotated slowly. When the mark on
the gear is centered in the viewing hole, the No. 1 pis-
ton is at the 22"
c.
0"
2" ETC
position.
Re m ove the ins pectio n hole
netos.
6-22
plugs from
the mag-
engaged, opening of the points
delayed ap proxi mately 26".
h’
Turn the crankshaft
will be
few
degrees counterciockbring
again
timing marks are
alig ned. At th is point both tim ing lights should go out
at the same instant that the timing mark on the crankshaft flange aligns with the crankcase parting surface,
or the timing mark on the alternator drive
gear
appears in the center of the cran kcase inspection
wise and
it back
a
until the
hole.
El 5
~eechcraft
BARON 55 AND 58
SHOP MAN UAL
i.
If the timing lights do not go out at the same time,
loosen the magneto that is late or early and repeat the
process outlined in steps g and h earlier.
poi nt kit and pry the points into the position wh ere any
further rotation of the cam will begin opening the
points. Retighten the contact kit screws and check the
spring to make sure it is located in the
distributor lead
MAGNETO BREAKER POINT
ADJUSTMENT OF SLICK MAGNETOS
The amount of
opening
between the
points should not
ad] usting the magneto contact points, since a weak spark will result if the opening of the contact points is not in time with the occurbe used
as a
method for
of the "E" gap. The proper "E" gap is obtained
when the timing pin is in place th roug h the hole in the
rence
frame and rotor shaft of the magneto. With the timing
pin is inserted in place, the rotor is in position for the
opening the contact poi nts. To adj ust the
points correctly, loosen the screws securing
contact point kit to the rotor bearing p late. I nse rt a
cam
to start
center of the distributor shaft hole in the distributor
bearing plate. Before removing the timing pin and reinstalling the distributor block housing on the magneto
frame assembly, apply a drop of SAE 20 lubricating oil
to the oilite bearings.
CYLINDER DIFFERENTIAL
COMPRESSION CHECK
A
cylinder differential compression check should be
accomplished at each 1 00-h ou r i nspection or when it
is suspected that the cylinders have become worn or
contact
have dam ag ed
the
accom
screwd river into the notch at the base of the contact
E15
pi ish ed
com pone nts. The check may be
i n accordance with Continental Service
Bulletin M73-1 9
or
subseq uent
bulletins.
6-23
aeechcraft
BARON 55 AN D 58
SHOP MANUAL
CHART G-6
TROUBLESHOOTING THE ENGINE
Th e tro u bleshooti ng chart is provided as a guide. Review all probable causes
given; check other listings of
trouble with sim i lar sym ptom s. The items are presented in the seq uence of approxim ate ease of
checking, not
necessarily in the order of probability of occurance.
Indication
1
Engine
Probable Cause
will not start.
a. no
to
fuel gage pressu re
Remarks
(No fuel
engine).
Check fuel control for proper
a.
position, with auxiliary pump "ON" and
operating, feed valves open, fuel filters
open, and tank fuel level.
b. Have gage pressure
(engine
flooded).
b. Turn off
switch,
auxiliary pump
and
ignition
set throttle to full open and fuel
control to idle cut-off, then crank
engine to clear cylinders of excess fuel.
Repeat starting
c.
Have gage pressure
(no
fuel to
engine).
2.
Engine
running
starts but fails to
keep
a.
Inadequate
fuel to fuel manifold
valve.
process.
Check for bent or loose fuel lines.
Loosen one line at fuel nozzle; if no
fuel shows, replace fuel manifold valve.
c.
Set fuel control in "FU LL RICH"
a.
position,
turn auxiliary pump "CN";
check to be sure feed lines and filters
are not restricted. Clean or replace
defective components.
b. Defective
ignition system.
b. Check accessible ignition cables and
connections. Tighten loose
con nections. Replace defective spark
plugs.
3.
Engine
runs
rough
at idle.
a.
Im proper id le mixture
adjustment.
Readjust idle setting. Tighten
adjustment screw to lean mixture and
back off adjustment screw to richen
a.
mixture.
b. Fouled
spark plugs.
b. Remove and clean spark plugs,
gap. Replace defective spark
adj ust
plugs.
4.
Engine
has poor acceleration.
a.
I d le
m ixtu re
too lean.
a.
Readj ust
id le
m ixtu re as
descri bed i n
3a.
b. Incorrect fuel-air mixture, worn
control linkage, or restricted air
cleaner.
c.
6-24
Defective
ignition system.
b.
Tighten loose connections, replace
elements of linkage. Service air
worn
cleaner.
Check accessible ignition cables and
connections. Replace defective plugs.
c.
El 5
BARON 55 AND 58
S HO P MAN UAL
CHART 6-5
TROOBCESH06Tjli(G
Indication
5.
Eng i ne
ru ns
rough
at
THE ENGINE
(Continued)
Probable Cause
speeds
a.
above idle
I m proper fuel-air
Remarks
m ixture
b. Check manifold connections for
leaks. Tig hten loose connections.
Check fuel control linkage for setting
and adjustment. Check fuel filters and
screens for dirt. Check for proper pump
pressu re, and replace pump if
defective.
b. Restricted fuel nozzle.
c.
Ignition system
and
b. Rem ove
spark plugs
defective.
6. En g i ne lacks powe r, red u ction
in maxim um manifold pressure at
critical altitude,
a.
an d
clean all noules.
Clean and regap spark plugs. Check
cables for defects. Replace
defective com pc nents.
c.
ignition
Incorrectly adj usted
th rottle
control, "sticky" lin kage
or
dirty
cleaner.
b. Defective
ignition system,
Check
movem ent of linkage by
control from idle to full throttle.
Make proper adjustments and replace
worn components. Service air cleaner.
a.
ai r
moving
b. Inspect spark plugs for fouled
electrodes, heavy carbon deposits,
eroded electrodes, im properly adj usted
electrode gaps, and cracked
porcelains. Test plugs for regular iiring
under pressure. Replace damaged or
misfiring pi ugs. Spark plug gap
sh ou id
be 0. 018 to 0.022 inch.
c.
Loose
or
dam ag ed intake
manifolding.
d. Fuel nozzle defective,
Inspect entire manifold system for
possible leakage at con nectio ns.
Re place dam aged com pone nts, tig hten
all connections and clamps.
c.
d. Check for restricted nozzles and
lines and clean
or
replace
as
necessary.
7. Low fuel pressure.
a. Restricted flow to fuel
valve.
metering
Check mixture control for full travel.
Check for restriction in fuel filters and
lines, adjust control and clean filters.
a.
Replace damaged parts.
b. Fuel control lever,
b. Check operation of th rottle control
and fo r possible contact with cooling
shroud. Adjust as required to obtain
correct
c.
Incorrect fuel i njector pu m p
adj ustment
and
d. Defective fuel
relief valve.
8.
High
fuel pressure.
a.
injector
Restricted flow
control
El 5
operation.
assem
bly.
pump
beyond
fuel
operation.
Check and adj ust using appropriate
equipment. Replace defective pumps.
c.
d.
Replace
pum p.
a. Check for restricted fuel nozzles or
fuel m an ifold valve. Clean or replace
nozzles. Replace defective fuel
manifold valve.
6-25
I
Qeechcr~ft
BARON 55 AN D 58
S HOP MAN UAL
CHART 6-5
TR6U B LESH ObTI NG TH E ENG I N E (Continued)
Indication
Probable Cause
b. Defective relief valve
in fuel injector.
operation
b.
Replace
fuel
Restricted recirculation
passage in fuel injector pump.
c.
Replace
pum p.
a. Vapor in fuel system,
fuel tem perature.
a.
Normally operating
c.
9.
Fluctuating
fuel pressu re.
b. Fuel gage line leak
gage line.
c.
or
excess
10. Low oil pressure on engine
or high oil tem perature.
injector pump.
the
auxiliary
pump will clear
system. Operate
auxiliary pump and purge system.
air in
Restriction in vapor separator
vent.
gage
Remarks
a. Insufficient oil in oil sump, oil
dilution or using improper grade
oil for prevailing ambient
b. Drain gage line and
connections.
tig hten
Check for restriction in ejectorjet of
vapor separator cover. Clean jet with
solvent (only). Do not use wire as
probe. Replace defective parts.
c.
a.
Add oil
or
change
oil to proper
viscosity.
temperature.
b. Defective
c.
ve math e rm
valve.
Oil cooler restriction,
d. Leaking, damaged,
line connection,
or
b. Check for-~efective vernatherm
valve. Replace valve if defective.
c.
loose oil
Clean oil cooler.
d. Check for restricted lines and loose
connections and for partially plugged
oil filter. Clean parts, tighten
connections and replace defective
parts.
11. Poor
5-26
engine idle
cut-off.
e.
Low oil pressure.
e.
a.
Engine getting
Check fuel control for being in full
"IDLE CUT-OFF" position. Check
auxiliary pump for being "OFF". Check
for leaking fuel manifold valve. Replace
defective com ponents.
fuel.
Readjust
oil pressure
as
necessary.
a.
515
SECTION
PROPELLER
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLERS
propellers are of the constant speed full feathering type. Feathering the propeller is accomplished
by pulling the propeller control levers into the full feather position, thereby releasing governor oil pressure, allowing
the countenveights and feather spring to feather the propeller blades. A port in the governor is opened by pulling the
drain back into the engine.
governor control levers into the full feather position and allows the oil from the propeller to
Average feathering time is between three and ten seconds.
The Beech Baron
NOTE
The
For
and
unfeathering
airplane
must be
starting procedures, refer
REMO VING THE PROPEL LER
Remove the
a.
equipped
with like
to the
propellers
applicable
of the
Pilot’s
same
Operating
manufacturer.
Handbook.
(MCCA ULEY)
spinner dome retaining
screws
and
remove
the
spinner dome.
If the
airplane
is
equipped
with the
alcohol anti-icing system, remove the spray nozzle retaining screws and disconnect the rubber tu bing before removing the spinner dome retaining screws. Remove the spinner dome support, and shims if installed, from the mounting
post.
3/4-inch wrench,
b.
Using
c.
Remove the
a
propeller
remove
and
the six
propeller
nuts.
O-ring.
NOTE
Use clean rags to plug the ce nte r of the engine crankshaft and p rope lie r h u b to p revent fo reign
material from contaminating the engine or propeller.
INSTALLING THE PROPELLER
Make
a.
sure
the
coat of
b.
Apply
a
c.
Apply
another
d.
six
light
propeller
light
and
engine
coat of
(MCCA ULEY)
engine flanges
oil to the
engine
are
and in stall the
O-ring
oil to the
clean.
O-ring
O-ring
in the circular groove of the
and to the inner surfaces of the
Apply a liberal coat of grease (A-1637-16, supplied with a new propeller,
mounting studs and to the threads and faces of the six mounting nuts.
or
propeller
MIL-T-83483)
propeller
hub.
hub.
to the threads of the
NOTE
possible to install the propeller in either of two positions
position is with one blade aligned directly over the T/C mark
It is
e.
propeller on the engine
mounting nuts, then apply
grease after torquing.
Position the
Install the six
excess
f.
Prepare
the
spinner dome
inch P/N 83281-1 shims,
one
with
a
one
wet
for installation
blade
on
the crankshaft
flange.
aligned directly over the T/C mark on the crankshaft flange.
600 inch-pounds to the mounting nuts. Wipe off any
torque of 540
by cleaning
inspecting for cracks, etc. Install two 0.016
spinner support on the mounting post. Lig htly
alignment of the spinner attach holes with the spin-
the surf ace,
0.032 inch P/N 83281-2 shim and the
press the spinner against the support and hold snug to check the
ner bulkhead. Misalignment of 3/64 inch is permissible.
El 6
relative to the crankshaft. The correct
7-1
BEECH BARON 55 AN D 58 SHOP MAN UAL
installation of fou r eq ual ly
pressure, push hard on the spinner just enough to allow the
it is just possible to install
until
shims
holes.
Remove
as necessary
screws and washers in the attach
of
the
circumference
around
the
spinner. Relax the force and
the four attach screws and washers all equally spaced
45
40
to
attach
the
screws
inch-pounds. If the airplane
install the remaining screws and washers. Torque
spinner
Using two
spaced attach
g.
men
for
even
equipped with alcohol anti-icing, install
spinner dome.
is
REMO VING THE PROPELLER
a.
Remove the
spinner
dome
b.
Remove the six bolts
c.
Remove th e p repel le r.
(HARTZELL)
retaining
nuts
or
the rubber tubing onto the spray nozzle and install the spray nozzles to the
screws
attaching
the
and
remove
propeller to
the
the
spinner
dome.
engine flange.
NOTE
Use clean rags to plug the engine c ran ks h aft and
contaminating the engine or propeller.
INSTALLING THE PROPEL L ER
a.
Clean the
propeller
hub to p reve nt fo rei g n mate rial f ro m
(HARTZELL)
propeller and engine flanges, removing
any
possible
nicks which would prevent proper
mating of the
s u rf aces.
NOTE
Before in stallation of the
with
engine
propel ler,
I ub ricate the
O-ring
in the circular g roove of the p re pel le r hu b
(2, Consumable M ate ri als C ha rt).
oil
b.
Install the
O-ring
c.
Install the
propeller
on
the
on
engine crankshaft flange.
the
engine flange.
NOTE
Wh en i nsta I ii ng th e p ro pe I le r, ai ig n th e No. 1 blade
directly
over
the T/C mark
on
the crankshaft
flange.
d.
Install the six bolts
p lane
e.
se ri als
or
Install the
spinner
attaching the propeller to the engine flange. Torque to 720
Torque to 840 960 inch-pounds for airplane serials TE-1 and
nuts
TC-1 and after.
840
inch-pounds
for air-
after and TH-1 and after.
dome.
NOTE
spinner to spinner bulkhead should be misaligned with the bulkhead at least 1/2 hole aft of the
spinner. The spinnerbulkhead should be pulled forward to install the attach bolts. This causes a
desired preload on the spinner.
The
For
7-2
propeller slip ring Removal and installation
see
Utility Systems,
Section 11.
E16
BEECH BARON 55 AND 58 SHOP MAN UAL
PROPELLER GO VERNOR
PR O PE LLER G OVE RN O R RE MOVA i,
a.
Ensure that the
b.
Remove the lower
propellers
are
in the unfeathered
(low pitch) position.
engine cowling.
engine baffling just forward
of th e prope I le r gove mor.
c.
Remove the
d.
Remove the cotter
e.
Disconnect all electrical wiring to the governor.
pin, nut,
washer and bolt
attaching
the
adjusting
rod end to the governor.
CAUTION I
I cnuTloN
airplanes with synchronizers, the magnetic pickup wires and the governor coil
interchangeable. Tag and identiljl all electrical wires to facilitate later installation.
On
f.
wires
are
not
Disconnect the oil line from the governor.
g.
Remove the four governor
h.
Cover the
engine
attaching
nuts and remove the governor.
boss.
PROPE LLER GOVERNOR iN STALLATION
a.
Remove the
cover
from the
engine boss; wipe the engine pad
clean and install
a new
governor
mounting pad
gasket.
CAUTION 1
I cp~unoa
Make
so
sure
the
gasket is placed on
that it will fit into the
recess
the governor spline with the
nuts to 216 264 inch-pounds.
the
engine mounting pad with
the raised side of the
screen
up
in the base of the governor.
engine
drive
and install the washers and nuts.
b.
Align
c.
Connect the oil line to the governor.
d.
Reconnect the electrical wires to the governor. These wires should have been
spline,
properly
Diagonally torque
identified
during
the
remov-
al.
e.
Install the bolt, washer, nut and cotter
pin attaching
the
adjusting
rod end to the governor.
NOTE
To
f.
El 6
ensure
I nstall the
proper
e ng i ne
adjustment,
do not turn the
adjusting
rod end when
installing
on
the governor.
baffli ng just fo rwa rd of the propeller governor.
7-3
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLER G O VERNOR A DJUS TMENT
FIG URE 7- 1
HIGH R P M A DJ U STM E NT
if it exceeds
rpm adjustment must be checked while the airplane is in flight. Observe the takeoff rpm to see
the redline figure. If excessive rpm is observed, land the airplane and adj ust the h i g h rpm screw i nward to reduce
the rpm to the redline figure. The high rp m adjustment screw is located at the front of the g ove m o r j u st fo rwa rd of
the speed adjusting control lever. One complete revolution of the screw reduces the propeller rpm by approximately
The
high
25
30 revolutions.
FEATHERING ADJUSTMENT
I
adj ust the featherin g action, pu II th e control slowly back through the detent and obs e rye the point at which the
at which propeller feathering
rpm setting begins to fall off sharply, then bring the propeller back to low rpm. The point
end of the governor control
the
on
is
the
screw
starts should be at 1850 rpm. If adjustment
square-head
required turn
will
lower the feathering rpm
inward
the
One
half
utio
of
I
screw
revo
n
shaft i nwa rd or outward to correct the setting.
approximately 100 revolutions. (See Figure 7-1.)
To
LOW R P M ADJ USTM E NT
FIGURE 7-2
Th e low rp m adj u stm e nt is made while the airplane is on the g ro u nd. To make this adj ustment, pu I I the propeller
lever back against the detent and observe the rpm setti ng. If the rpm vari es from the specified low rpm setting of
2,000 rpm, the low rpm setting must be adjusted. The low rpm adjustment is made on the detent rod which is located
behind the instrument
the
setting,
panel
on
the governor control
linkage.
To increase the
setting,
shorten the rod. To decrease
len gthen the rod.
PROPE LLER FEl\tHERING
SCR EW
p
~ADJUS T~M ENT
HIG\H RPM’APJ II STM ENT
SCR
EW~
O
PR’OPEILER
GOVERN C)R
681-264-7
Propeller Governor Adj ustment
Figure
7-4
7-1
E16
B E EC H BARON 55 AND 58
SHOP MAN UAL
TH 4 6 7 A ND
PROPELLER SYNCHRONIZER (TC- 1 710 AND AFTER; TE-98 I AND AFTER;
AFTER, EXCEPT TH-4 73 AND TH-4 74)
of the two engines. When the rpm of one engine
optional propeller synchronizer automatically matches the rpm
This limited range prevents eichanges, the other will automatically follow the change over a predetermined range.
is feathered while the propeller
ther engine from losing more than a fixed amount of rpm in case the other engine
The
sync h ro n ize r remains O N.
is transmitted to a transistorized
A slotted disc in each governor passes a magnetic pick-up and an electrical impulse
in pulse rates and changes the
difference
the
control box installed behind the pedestal. This control box measures
each engine is equal. The proof
until
the
rpm
coil voltage of each governor
governor speed setting by varying the
lower
the
pedestal.
pelle r synchronizer may be tu med O N by a toggle switch located on
the synchronizer ON. The propelTo operate the system, synchronize the propellers in the normal manner and turn
both propeller controls at
ler rpm of each engine will automatically adjust to the same rpm. To change rpm, adjust
the synchronizer. If the
of
limited
range
the same time. This will keep the propeller rpm of each engine within the
the
outside
is
synchronizer range.
synchronizer is ON and the propeller rpm will not synchronize, the propeller rpm
the
and
turn
synchronizer ON.
Turn the synchronizer OFF, readjust the rpm of each engine manu ally to equal rpm
PROPELLER
CO NTR OL LEVERS
LOW RPM
ADJVSTMEN‘T
58P248´•11
Propeller
Low RPM
Figure
E16
Adjustment
7-2
7-5
BEECH BARON 55 AN D 58 SHOP MAN UAL
SYNCHRONIZER FUN CTIONAL TEST
the proProper operation of the propeller synchronizer can be determined by the following method. Manually adjust
either
small
in
increments,
propeller control levers to equal rpm. Turn the propeller synchronizer ON. Slowly adjust,
limited range
peller governor to increase or decrease rpm. The rpm should remain synchronized over a
25 rpm difference bepredetermined by the synchronizer. Turn the synchronizer OFF and establish a maximum of
of
both engines should
the
and
N
rpm
tween the engine rpm of the left and right engines. Turn the sync h ron ize r O
synchronize.
SYNCHRONIZER CHECKS
These checks will
help
locate the
source
of trouble should the
synchronizer system malfun ction. If no malfunctions
probably the source of trouble. An ohmme-
tested, the transistorized control box is
found among the units being
ter, voltmeter and oscilloscope are
are
required
to conduct the tests below.
SYNCHRONIZER WIRING CHECK
a.
To eliminate the most obvious
that the
causes
for malfunction make
propeller synchronizer circuit breaker is not tripped,
plug in the airplane electrical system.
sure
airplane battery master switch is ON,
modified Jones plug receptacle is properly
that the
and that the
mated with the
Unplug the control box, turn the airplane master switch OFF,
before proceeding further with these checks.
b.
c.
Complete
the
and
pull
the
propeller synchronizer circuit
breaker
following resistance checks: (See Figure 7-2A.)
CAUTION I
[cnvnow
Zero the ohmmeter and read on the X1 or X10 scale during the following checks. Do not use a probe
avoid damaging the
greater than 0.045 inch in thickness. insert and remove the probe carefully to
pin
connectors.
NOTE
Readings
7-6
may be 20
percent higher during heat soak fol lowi ng engine shutdown.
1.
Check the resistance between
pin
1 and
airplane ground.
The ohmmeter should indicate 0 ohms.
2.
Ch eck the resistance between
pin
2 and
airplane ground.
The ohmmeter should indicate
3.
Check the resistance between
pin
3 and
airplane ground.
The ohmmeter should indicate 52
4.
Check the
between
pin
4 and
airplane ground.
The ohmmeter should indicate
5.
Check the resistance between
pin
5 and
airplane ground.
The ohmmeter should indicate 52
6.
Check the resistance between
pin
6 and
airplane ground.
The ohmmeter should indicate
an
open circuit.
7.
Ch eck the
res istance
between
pin
7 and
airplane ground.
The ohmmeter should indicate
an
open ci rcu it.
8.
C heck th e
res i stan ce
between
pins
res istan ce
4 and 7. The ohmmeter should indicate 1 12
an
open circuit.
68 ohms.
an o pe n c i re u it.
68 ohms.
138 ohms.
E16
SEECH BARON 55 AND 58 SHOP MAN UAL
9.
1 O.
porates
d.
Ch eck the resistance between
138 ohms.
6 and 7. The ohmmeter should indicate 112
Check the resistance between pins 7 and 8. The ohmmeter should indicate 23
resistor and a fuse between these pins.
27 ohms. The
plu g
in co r-
a
Tu m the
co ntrol
pins
box
airplane
batte ry master switch ON, and reset the
propeller synchronizer ci rcuit breaker,
but leave the
u np I u g g ed.
the de voltmeter, check that the voltage between pin receptacles 1 and 2 is the
age, and the polarity of pin nu mbe r 1 is negative while that of pin number 2 is positive.
e.
Using
f.
Using an oscilloscope,
check the
voltage
between
pins
5 and
same as
the
supply
volt-
1, and 3 and 1. With the engine operating at cruise
rpm, the oscilloscope should indicate 3.0 volts, peak to peak. The voltage should not read less than 2.0
at minimum cruise rpm nor more than 10.0 volts, peak to peak, at maximum cruise rpm.
peak to peak,
NOTE
These
readings are based
If adjustment
0.005 inch.
adj ustme nt
is
p rocedu res.
When the system is in
system and flight check.
g.
magnetic pickup/toothed w h ee I cl ea ran ce gap of app roxi mate ly
required, refer to the Woodward Test Specification SP-1 97 for
on a
compliance with the preceding
check values,
plug the control
box into the
synchronizer
FLIGHT CHECK
Check the effect of rpm and/or power setting, particularly in the lower cruise range on synchronizer action. If
operation at lower rpm results in improved synchronization, inspect the drives to the governors.
a.
b.
Reduce the electrical load and turn off the generator and all other electrical units, except the master switch and
If synchronizing improves, abnormal voltage spikes on the airplane bus from some other electrical ac-
synchronizer.
cessory may have been upsetting the
in the control box, replace it.
synchronizer.
Isolate the
offending
accessory and
8
6
4
2
7´•
5
3
1
repair
it. If the trouble lies
VIEW OF CONTROL 80X CONNECTOR
SHOWING N UM 8 E 8 6 D T ER M I NA LS
58P´•35~-2
Synchronizer Plug
Figure 7-2A
E16
7-7
BEECH BARON 55 AND 58 SHOP MANUAL
PROPELLER A CCUMULA TOR REMO VAL
(FOR AIRPLANES WHICH A RE EQUIPPED WITH THE UNFEA THERING ACCUMULA TOR)
a.
Check the
b.
Open
the
propeller control
access
door
on
lever for the low
pitch position
the inboard side of the nacelle
in order to release the accumulator pressure.
immediately
aft of the firewall, to
gain
access to
the
accu mu I ato r.
c.
Remove the accumulator line from the end of the accumulator.
d.
Remove the four attach bolts and attach bracket from the accumulator and
remove
the accumulator from the
airplane.
Installation is the
reverse
of the removal
proced u res.
NOTE
The pressure in the accumulators should be maintained at 100 ~5
accumulators, use commercial dry air or nitrogen.
psi.
When
inflating the
PROPELLER A DJUS TMEN T
High and Low pitch adjustments, service,
applicable FAA App roved P repel re r Man uals.
For
overhaul and maintenance
procedures,
refer to the manufacturers
MINOR PROPELLER BLADE REPAIR
FIG URE 7-3
Minor nicks, dents, and gouges may be dressed out by approved personnel. Blend any nicks or gouges into the
th
leading edge with smooth curves, and generous radii as shown in Figure 7-3. Reanodize reworked a reas by e
chromic acid process
only.
s~
~i::::
-~e
A
A
SECITION A-A
Minor
7-8
THOOB
984863AA
Propeller Blade Repair
Figure 7-3
E16
BE ECH BARON 55 AND 58 SHOP MAN UAL
TROUBLESHOOTING
PRO P E LLER SYN CH RO N IZER
1
Synch ron izer i noperative.
Circuit breaker trips.
a.
b. Intermittent
1
3
also
or
1
5
readings
(circuit
on
pins
breaker may
repairfaulty component.
a.
isolate and
or open
picku p in gove rno r.
b.
Repair
or
replace magnetic pickup.
or grounded wire in
pickup in governor.
c.
Repair
or
replace magnetic pickup.
grounded wire in
magnetic pickup in governor.
d.
Repair or replace
magn etic
e.
Repair or replace
broken wire
a.
Short in
airplane wiring.
b. Intermittent short
mag netic
trip).
Left governor pickup gives
or short circuit reading on
c.
open
pins
d.
1
e.
governor pickup gives
short circuit reading on
Right
Left governor coil
sho rt
reading
on
gives open
pins 6 7.
f.
Right governor coil gives open
7.
or short reading on pins 4
2. Poor
a.
c.
B ro ke n
mag netic
5.
open or
3.
pins 1
or
REMA R KS
P RO BA B LE CAU S E
TROUBLE
d. Broken
or
Broken
or
e.
wire in
grounded
coil. Coil defective.
f. Broken
or
pickup.
or
replace
governor.
grounded
wire in
coi I. Coil defective.
f.
Repair or replace
broken wire
or
replace
governor.
synchronization.
Pickup voltage
exceeds 3.0
volts at cruise rpm.
a.
I nsufficie nt
picku p
pickup to give specified voltage
output. (See Woodward Governor Bulletin
to
a.
flyweig ht head clearance.
Reset
No.
33117.)
3. Oil leaks from mag netic picku p
connection in governor body.
a.
Defective
pickup
O-ring between
a.
Replace.
b.
Replace.
c.
Tighten
d.
Replace pickup.
and lock nut.
b. Defective
gasket under
lock
nut.
c.
Nut loose.
d. Defective
pickup.
I
CAUTION
cnuTloN
to 25
inch-pounds.
I
See Woodward Governor Bulletin No. 33 1 1 7. Never turn
pickup into flyweight hea d.
Check
voltage
output.
E16
7-9
SECTION
FUEL SYSTE NI
FUEL SYSTEM
The fuel selector valve for each
ment.
Se rvice all fuel systems with aviation gasoline, 100 LL
(Blue) preferred or 100 (Green) octane minimum grade.
tor
and
handles. Two fuel
panel indicates
level
quantit y
indicators
the amount of fuel in each
o pe ra t i o n
crossfeed
TC- 1 THRU TC- 1607 AND TE- 1 THRU TE-942, EXCEPT TE-938
engine is located
during normal o pe rat ion, fue I i s con
sumed from each wing system as indicated by the fuel selec-
panel
below this
is
u se d
d u ri ng
on
the i nst ru me n t
wing system. Fuel
e me rgenc
y condi t ions i n
flight only.
serials TC- I thru TC- lh07 and TE- I thru TE-94?.
8 snap-type drains (4 per wing) are provided. One drain in
each wing is provided for the inboard wing leading edge fuel
except TE-93X are equipped with a non-interconnected fuel
s ys te m. The main and auxiliary cells in eac h wing provide
cell sump: fuel strainer: wing box section fuel cell sump: fuel
system low poi nt (i n wing).
Airplane
capacity of either 11Z gallons
gallons (136 gallons usable).
These systems have either 75 or 40 gallon baffled or unbafTied i n boa rd wing leading edge main fuel cells with a fi nge r
strainer in e ac h i nboard wing leading edge, and a 31 gallon
au x i I iary fuel cell with finger s t ra i ner i n each wing box
section. Thus, there is a total of either 53 or 68 gallons usable
in each wing for a total of either IOh or 136 gallons usable
the
(106
airplane with a total
gallons usable) or
fuel
142
with all fuel cells full. One flush-t y pe filter cap is in each
inboard wing le ading edge and one flush-type filler cap is
I ocat ed i n t he outboard end of
eac h
wing
box section cell.
TE-938, TE-943 THRU TE- 1083 EXCEPT TE- 1081
Airplane
se
rials TE-93X, T E-943 thru TE i 083,
e x ce pt
TE
equipped with interconnected fuel cells in each
wing to provide the airplane with a total fuel capacity of
1 66
I 36 gallons usable) or 1 77 ga i ion s
e ither 1 42 gallons
I
I
i
fue
s forw ard of
ne
for
the
ne
engi
usable).
Except
gallons
the firewalls, the 147, gallon total capacity system is the same
I OX I
as
are
described under the
heading TC- 1608
TH R O U G H TC
3002, EXCEPT TC- 1970 in this section.
A fuel selector
spar
panel
in the cabin fu se lage
between the front seats. is
cover
i n front of the
placarded OFF-AUX-
M A I N -C R OSS FE E D for fuel manage me n t The fuel selector valve for each e n gj ne i s loc ated below this pa ne I an d
during normal operation fuel is consumed from the fuel cells
in each
wing
as
indicated
by
the fuel selector handles. Two
panel indicate the
a mou n t of fuel i n e it her the main or auxiliary fuel cells for
their respective wings. A two position fuel cell selector
switch on the pilots sub-panel determines the fuel cells, main
or auxiliary, to which the fue 1 quantity indicators are connected. Fuel may be used as desired during le vel flight,
fuel
quantity
indicators
on
howe ver, si nce fue I fro m
flight only,
sufficient
the instrument
au xiliar y
reserve
ce i is
must
be
mu st be used i n I e ve I
re ta i ned
i n the main
fuel cells for take-off, climb and
operation is used in these
t ion s i n ie vel fl ight onl y.
landing. Fuel crossfeed
systems during emergency condi-
17’ gallon system utilizes cells described in the 142
gallon system and an additional fuel cell in each outhoard
wing leading edge. This cell has a bottom mounted fue I le ve I
The
transmitter located in the inboard end of the cell. The cells
interconnected to provide 8B gallons usable in each wing
are
system
total of 166
a
or
gallons
usable with left and right
fu ii. One fl us h- t ype fi lier cap i s in t he
end of each outboard wing le adi ng edge cell.
wi ng
s yste ms
The
function for fuel
management and the fuel selector
fuel selector valves and fuel
panel,
ou t board
quantity
indicators
are
in
described for the 142 gallon total capacity system under the heading TC- lh08 THROUGH TC-2002.
EXCE PT TC-1970.
the
same
location
as
NOTE
X snap-type drains (4 per
each
wing
is
provided
wing)
are
prov id ed. One drain in
for the inboard
Fuel crossfeed
wing leading edge fuel
tems
cell sump: f~uel strainer drain: auxiliary fuel cell sump; fuel
system low point in each side of cabin fuselage bottom.
during
operations
are
used in these sys-
emergency conditions in level
flight
only.
TC- 1608 TjYRU TC-2002, EXCEPT TC- 1970
8 snap-type drains (4 per wing) are provided. One drain in
each wing is provided for the inboard wing leading edge fuel
Airplane serials TC- 1608 thru TC-2002, except TC- 1 970, are
equipped with an interconnected fuel system. The tanks are
interconnected within each wing and provide the airplane
with a total fuel capacity of 142 gallons (136 gallons usable).
This system has an inboard wing leading edge unbaffled fuel
cell with fuel reservoir, finger strainer and fuel outlet nipple
through the wing root rib that is interconnected to a wing box
section fuel cell for 68 gallons usable in each wing system or
a total of 136 gallons usable with left and right wing systems
cell
full. One flush type filler cap is located in the outboard end
wing box section cell. A fuel selector panel, located in
of the
the cabin
seats, is
between the front
cover
fuselage
placarded OFF-ON-CROSSFEED forfuel
in the front spar
manage-
su
mp: fuel strainer:
system low
wing
point tin wing).
box
sec
tion fuel cell
sum
p: fue I
TH- 1 THRU TH-384
are equipped with interprovide the airplane with a total
fuel capacity of either 142 gallons (136 gallons usable) or 172
gallons 1 66 gallons usable). The 142 gallon to tal capac i t y
Airplane
connect
serials TH-I th ru TH-384
cells in each
system has
an
wing
to
inboard wing leading edge baffled fuel cell
with sump strainer and fuel outlet nipple through the inboard
end of the wing main spar. This cell is interconnected to a
8-1
wing box section
s
yste m
or
fuel cell for 68
total of 136
a
gallons usable in each wing
gallons usable with left and right
wing systems full.
One flush-t ype filler cap i s located i n t he
outboard end of the wing box section cell. A fue I se lec tor
pa nel
I oca ted
on
the cabin f u selage floor board for w ard of
the front spar cover, is placarded O FF-O N -C ROSS F E E D
for fuel management. Remote fuel controls in this panel are
attached
to
fuel selector valves in the wheel wells for each
engine. During normal operation, fuel is consumed from
each wing system as indicated by the remote fuel selector
ha nd le s i n the cabin fuselage. Two fuel quantity indicators
on the instrument panel indicate the amount of fuel in each
wing system.
The 172
gallon
total capac i t y system utilizes the cells de
scribed in the 142 gallon system and an additional fuel cell in
controls in this
panel
the wheel wells for
are
attached to fuel selector valves in
eac h
engine. During nor mal ope rat ion
wing system as indicated by the
remote fuel selector handles in the cabin fuselage. Two fuel
quantity indicators on the i nst ru me n t pa ne I i nd i cat e the
fuel is consumed from each
of f uel i n
amou n t
eac h s y s te m.
The
172 gallon total capacity system utilizes the fuel cells
described in the 142 gallon fuel system and an additional fuel
cell in each outboard wing I eading edge. This cell has a
bottom
mou
nted fuel level transmitter located in the i n board
end of the cell. The cells
gallons usable
in each
w
are
i ng
inte rcon nect ed to provide 83
or a total of I 66 gallons
s ys te m
usable with left and right wing systems full. One flush-type
filler cap is in the outboard end of each outboard
wing
leading edge cell.
each outboard
nected to
system
or
wing leading edge. The cells are interconprovide 83 gallons of usable fuel in each wing
a total of 166 gallons usable with left and right
wing systems full. One flush-type filler cap is in the outboard
nd of e ac h outboard wing leading edge. A fuel level trans-
a
mitter is mounted in the top of the outboard
edge fuel cell.
The function for fuel
w i ng
re ad i n g
management and the fuel selector
panel, remote fuel controls, fuel selector valves and fuel
quantity indicators are in the same location as described for
the 142 gallon total capacity system.
The 200
gallon total capacity sys tem (TH-6h9 th ru TH-777,,
except TH-766) utilizes the fuel cells described in the 1 72
gallon fuelpystem and an additional wet wing tip fuel tank on
each wi ng. The
yste m i s i nterc on nec ted
to provide 97 galwing system or a total of 194
gallons usable with left and right wing systems full. One
flush-type filler cap is in each wet wing tip tank in addition to
the flush-type filler cap in the outboard end of each outboard
wi ng lead ing edge cell for the 1 77, gallon ca
pac i t y s y s t e m.
s
ions of usable fuel in each
CA U~ON
N OT E
Fuel crossfeed
tems
during
operations
When
are
used in these sys-
emergency conditions in level
provided with
The
su
wing)
mp; fuel strainer;
wing
provided. Each wing is
wing leading edge fuel cell
are
I drain for: inboard
s
vs re m,
re mo v e
the out-
flight
only.
6 snap-ty pe drains (3 per
servicing this
board cap first to prevent loss of fuel if it is
above the level of the inboard cap.
box section fuel cell sump,
fu nc t ion
for fuel
management and the fuel
sele~tor
panel, remote fuel controls, fuel selector valves and fuel
quantity indicators are in the same location for the 172 or ’00
gallon total capacity system as described for the 142 gallon
total capacity system.
TH-385 THRU TH-772, EXCEPT TH- 766
N OT E
Airplane serials TH-385 thru TH-772, except TH-766 are
equipped with an interconrtected fuel system. The cells are
interconnected within each wing and provide the airplane
with a total fuel capacity of 142 gallons 1136 gallons usable),
172 gallons (166 gallons usable), or 100 gallons (194 gallons
usable).
Fuel crossfeed
tems
during
operations
are
used in these sys-
emergency conditions in level
flight
only.
Airplane
serials TH-3X5 thru TH-777,
except TH-76h, with
or 172 gallon total
capacity fuel system, are
equipped with a total of 6 snap-type drains (3 drains per
wing). Each wing is prov~ded with I drain for the in boa rd
either the 147
The 142
gallon total capaci ty system has an inboard wing
leading edge unbaffled fuel cell with a fuel reservoir, finger
strainer and fuel outlet nipple through the wing root rib, This
cell is interconnected to n wing box section fuel cell for 68
gallons usable in each wing system or a total of 136 gallons
usable with left and right wing systems full. One flush-type
filler cap is located in the outboard end of the wing box
section cell.
A
fuel selector pa ne i, locate d
on
the cabin
fu selage floor forward of the front spar cover, is placarded
OFF-ON-CROSSFEED for fuel management. Remote fuel
8-2
wing leading edge fuel
cell sump; fuel strainer;
wing
box
section fuel cell sump,
Airplane serials TH-669 thru TH-773,, except TH-7hh equipped with wet wing tips (2~) gallon total capacity system)are
provided with a total of b snap-type and flush-type drains
(4 drains per
the inboard
wing). Each wing is provided with I drain for
wing I eading edge fuel cell sump: fuel strainer;
wing
box section fuel cell sump: wet
N OT E
wing tip (flush-type
drain).
Fuel crossfeed
during
tems
operations
are
used in these sys-
emergency conditions in level
flight
only
TC- 1970, ~C-2003 A ND A FTER
are p ro v ided. One
nap- ty pe d rai ns (3 drains per wing)
the inboard wing leading
e ac h wing is provided for
edge fuel cell sump; fuel strainer: wing box section fuel cell
6
s
drain in
equipped
and after
Airplane serials TC- 1970, TC-Z(H)3
interconnected fuel system, The cells which are
inte rcon nect ed within each wing, provide the airplane with a
with
an
This sy ste m has
gallons 1136 gallons usable).
of 1~42
capacity
total fuel
;rH-766, ~H- 773 A ND AFTER
inboard wing leading edge, baffled fuel
an
cell with sump strainer and fuel outlet nipple through the
inboard end of the wing main spar. This cell is intercon-
and
usable in
gallons
a wing
wing system or a total of 136 gallons usable with left
right wing systems full. One flush-type filler cap is
box section fuel cell for 68
nected to
each
wing
box section cell. A
the cabin
fuselage floorboard
located in the outboard end of the
fuel selector
panel,
sump.
located
on
Airplane
with
a
an
serials TH-766. TH-771 and after,
gal Ion
2.00
total
capacit y
384 except. the fue I
this pa ne I are attac hed to fuel se I ec tor valves in the wheel
we i I s for eac h engine. During normal operation, fuel is con-
of top
fuel
se
wing system
as
i ndic ated
by the
remote
lector handles i n the cabi n fu se lage. Two fue i q ua n t i t y
on the instrument pane I indicates the amount of
indicators
fuel in each
h
s
are provided. One
provided for: inboard wing leading edge
strainer; wing box section fuel cell sump,
is
wing
Fuel cell sump; fuel
mou
or
se nsor
i n the i nboard
e
nd of the
out-
is bottom mounted instead
nted
fuel system ut iii ze s t he cells
fuel
described in the 172 gallon
~y stem and an additional wet
is interconnected to provide
This
tank.
fuel
system
wing tip
The ~00
gallon
tot a I c:apac i t y
wing system, or ii total o f 1 94
left and light sys te ms full One flush
is in eac h wet wing tip tank in addition to the
gallons usable in
gallons usable with
nup-t y pe drai n s (3 drains per wing)
drain in each
17’
fuel sy ste m.
wing leading edge fuel cell
board
97
wing system.
a
the 142 and 177Airplane serials TH-766, TH-773 and
gallon total capacity systems are the same as the 142 and 17’
gallon sy stems described for airplane serials TH- I thru TH-
forward of the front spar cov er, is placarded O F F-ON
CROSSFEED for fuel management. Remote fuel controls in
sumed from each
equipped
are
OFF-ON-CROSSFE ED interconnected 142,
euc
h
Filler cap
flush type filler cap in the uutboard end of each outboald
leading edge cell for the 1 72 gallon sy ste m.
t y pe
panel, remote fuel controls, fuel selector
valves and fuel quantity indicators for the above systems are
in the same location as described for TH- I through TfI-77’1.
The fuel selector
~E- 1081, ~E- 1084 AND AFTER
except TH-766, fuel systems. The function for fuel manage
ment is also the same.
Airplane
with
an
serials TE- 108 I, TE-1084 and Lifter are equipped
OF F-ON-CR OSSFEED I 42 or a 177- gallon total
capacity fuel system. Except
firewalls, the 14?
the
gallon
1J?
gallon
total
total
for
engine lines forward of
capacity
system is the
capacity system described
NOTE
the
same as
un der
Fuel crossfeed
the
tems
head i ng TC 1 ’)70, TC -2007 A N D A FTER in this section.
177- gallon total capacity system utilizes the fuel cells
described in the 142 gallon fuel system and an additional
outboard wing le ading edge fuel cell on each wing. ~his
during
operations
are
used in these sys
emergency conditions in level
The
sy stem
provide 83 gallons usable in aach
of 166 gallons usable with left and
is interconnected to
wing system, or a total
I ight wing system full.
One flush type filler cap is in the
wing le adi ng edge cell.
outboard end of each outboard
flight
only
Airplane serials TH-766, TH-773 and
14? or 172 gallon total capacity fuel
af ter, with either the
sy stem
are
equipped
h
a total of 6 snap-ty pe drains (3 drains per wing). Eac
drain for t he i nboard w i ng ]e ad i ng
wing is provided with
edge fuel sump; fuel strainer; wing box section fuel cell
with
sump.
serials ~TH-76h, TH-773 and after, equip ped with
wing tips (20C gallon total capacity system) are provided
Airplane
The function for fuel management is the
same
and the fuel
wet
´•total of 6 snap-type and Z fl ush- t y pe drai ns (4 dra i n s
fur the i nboard
per wing). Each w ing is prov ided with I drain
box
w i ng le adi ng edge fuel cell sump; fuel strainer; wing
selector
panel, remote fuel controls, fuel selector valves arlcl
fuel quantity indicators are in the same location as described
for the 142 gallon total capaci ty system u nder the heading
with
TC- 1’)70, TC -?003 AN D A FT ER,
section fuel cell sump: wet
a
wing tip (flcish-type drain).
8-3
Airplane serials TC-l608 and after, TE-938, TE-943 and
after and TH-385 and after, are
equipped with a fuel level
si gh t gage located i n eac h w i
ng lead i ng edge ce II, out board of
the engine nac e I le The gages are to be used for
fue i oTf
loading and not to be used as fuel quantity indicators.
Being
an injection type system most fuel
malfunctions can
be attributed to contaminated fuel, therefore, the wheel well
mounted strainers, finger strainers and
sump strainen
s ho u id be i ns
pec t ed and c I ea ned regu larl y. Th e fre q u enc y uf
inspection and cleaning will depend upon service conditions,
fuel
handling equipment,
cleanliness and local sand and dust
conditions.
NOTE
i f Good year fue I eel i s, manu factured after I 96 I
(Cunstruction No. BTC-39, BTC-53A and ETC
h7) are installed, no preservation procedures are
necessary when the cell is to be empty for an
indefinite period of time. The fuel cell should
not be open to the atmosphere
except for the
normal vent lines in the
airplane. Goodyear fuel
prior to 19h i and Uniroyal
fuel cells must be filled
every ten days or the
walls coated with a thin coat of light
engine oil.
cells manufactured
FUEL SYSTEM CAPACITIES
FUEL CA PA Cl TY
AIRPLANE SERIAL
FUEL SELECTOR POSITIONS
CAPACITY
TC- I thru TC- I 607,
O FF- A U X M A i N -C ROS S FE E D
I I 2 Gallon,
Non-interconnected.
TE-I thru TE-941,.
except TE-938
Capacity System
i 06 Gallon
Usable)
TC- 1
t h ru
TC- 1 607
O FF- A tl X- M A I N-C R OSS FE E D
TE-I thru TE-942,
142 Gallon,
N on In te re o n n ec te d
except TE-938
Capacity System
(136 Gallon)
Usable)
TC- 1 608 and after;
TE -93 8, TE -943 and
O FF-ON -CR OSS FE E D
after; TH-I and
1 42 Gallon,
Interconnected,
Capacity System
after
(136G allon
Usable)
T E-938, TE -943 and
O FF-O N -CROSS FE E D
after: TH-I and
1 72 Gallon
Interconnected,
Capacity System
after
(166 Gallon
Usable)
TH-h69 and after
With Wet Wing Tips
OF F-ON-CR OSSFEED
200 Gallon,
Interconnected,
Capacity System
(194 Gallon
Usable)
8-4
II:
3
J
E~, ~7
S´•r
iC1~11
2
-Z~
3
Prior
to
TC-251
TC-251 thru iC-1607
FUEL STRAINER
Prior
to
’r
TC-251
iE‘1 thru TE-942.
TC-251 thru TC-1607
BOOST PUMP
except TE-938
TE-1 thru TE´•942.
except if-938
p
AUXILIARY TANK
DRAINS
QI ef
I
(L~iV
4
FLVSH IVPE VENT
I
2
~c_
c
RETURN LINE (AUXILIARYI
2-
i;
ENGINE DRIVEN FUEL PUMP
VALVES
RETURN LINE (MAINI
CHECK VALVE
TO FUEL GAGE
DISTRIBUTORi
METERING VALVE
55-281-22A
Figure 8-1. Fuel System (iC-l thru TC-1607 and
TE-? thru TE-942, except TE-938)
8-5
MAIN
RETURN
INLLI
ri
o
10
CROSS
INLET
;Eso
RETURN
CROSS
4uxluanv
FEED
aETunN
CONTROL
I$,
INLET
CONTROL
UNIT
NITCTOI
PUMP
UNIT
MAIN
RETURN
772
PUMP
ENGINE
MAIN
RETURN
SUPPLY
SELECTOR
tCHECK
*uxiLianr
PUMP
VALVE
1,
1
INI(ETOs
AUXILIARY
ENGINE SUPPLY
OUTLET
I
OUTLET
L.n.
-r’
ENGINE
,O
INLET
FEED
IEIUIN
-J;
XFU
~3
MAIN
ENGINE
RETURN
CROSS
´•i~J
?uxlllnRv
ENGINE
INLET
Ip‘
L
CROSS
AUXILIARY
INLET
ENGINE
FUEL
VALVE
CHECK VALVE
t
*uxiLinar
DRAIN
ETURN
SELECTOR
9,H.
VALVE
1
PUMP
GRAIN
STRIZINER
FUEL
STRAINER
PUMP
INJe croa
oRn~N
puMp
GRAIN
CHECX
VALVE
.~==i
CROSS
EL STRAI N ER
FEED
I’’’~
LINES
10
C~BIN
ilEATER
FUEL
i
1
auxi~iaiu
z
s
AUxIiIaaY
TC-251, TC-371, IC-JZ1
TC-251, TC-371, 1C-421
TnRU TC-1607 AND TE-1
I
;i)):
MAIN
TANK
MAIN
THRU 11.94.
1
CHECK
I
1
oaaln
i X CE PT T 3 93 8
II
’i
ITR~INER
’/aLVE
I ´•I ´•I I I ´•I II I I I I
I
I
II
I~1
I-
1~
aUXll(nRr
i -1
T H R U TC´•I b0 7. LN D TE-I
THRU TE- 94 2, i X CE PT TE
O
--~f?--:
VENT
i
I
t
TANK
CHECK
V
ALV L
IrIIIIIIIIIIIIII 1
-i
J
VENT
nUXRlnRY :ANK
InNKii
SELECTOR
CHECK VALVE
CHECK
./ALV(
VALVE
:g,o~:o´• 137 04L-IN
SUPPLY
GRAIN
i
RETURN
Imnrrrm~
)RAIN
~R
23 GALLON (22 GALLON
USABLE)
VENT
DRAIN
jS-603.28A
Figure 8-2. Fuel System Sc~ematic, OFF-ON-CF~OSSFEED,
(TC-1 thru TC-1 607, and TE-I thru TE-942, except iE-938),
8-6
938
I FUEL
RETURN
FUEL LINE
II
.FUEL
~IHEATER
FUEL SUPPLY
I
PUMP
1 VENT LINE
ER FUEL PUMP
’6 ITH FUEL F I LT E RS
FIFIEWALL
HE ATE R FUE L LIN E
FROM LEFT FUEL
CELL ONLY
I~/
11
t
FUEL LEVEL
SIGHT GAGE
EDGEI
FUEL SELECTOR
iii
VENT LINE
VALVES
FROM
LEUFTHGIRCELL
CHECK VALVE
FILLER
,FLAPPER
CAP
DRAIN
‘A
i~RAIN\
TO RIGHT
V
-c- ENGINE
CROSSFEED
I R\ESERVOIR
(FIN GER STRAIN ER
AUXILIARY
FU EL PUMP
rTC-1654 THRU TC-2 002 AND TE-964
~-DRAIN
PR~SSURE
SIPHON
RELIEF
VALVE
BREAK
THRU TE-1O83 DO NOT HAVE
F LA PPE R V A LVE
NAL
VENT
+TC-1608 THRU TC-1657 AND
(HEATED)
TE-938,
TE-943 THRU TE-967 EXCEPT TE-959
HASTWO FILTERED HEATER FUEL
PUM PS IN SER IES WITH A HEATER
SOLENOID VA LVE BETW EEN PUM PS
AND HEATER
Figure
8-3. Fuel
System
142 Gallon
Capacity,
(136 Gallons Usable, TC-1608 thru TC-2002 except TC-19 70,
TE-938, TE-943 thru TE-1083 except TE-1 081).
FUEL RETURN
I
F~ FUEL
LINE
~FUEL
SUPPLY
I
I
Il ~lnEATER
.FUEL
IBUTOR
PUMP
1 VENT LINE
HEATER FUEL PUMP
W ITH FUEL F I LT ER
MECHAN ICAL C ONNE CTOR
FIREWA LL
1
HEATER FUE L LINE
FROM LEFT FUEL
CELL ON LY
I
hr
1
FUE L LEVEL
SIGHT GAGE
FUEL SELECTORS
RESERVOIR
FINGE R STRAINE R)
EDG
CELL
CHECK VALVE
FILLER
CAP
c~ FR OM RIGHT
:ii
FUEL CELL
I
II
To
~NNET
CHECK
VALVE
t
AUXILIARY
II
LY-PRESSURE
RELIEF
VALVE
I FUEL PUMP
7_L~DRAIN
SIPHON
BREAK
II
VENT
(HEL\TED)
Figure
8-4. Fuel
System
142 Gallon
CROSS FE ED
RIGHT
ENGINE
R
TH-432 THRU TH-772 DO NOT HAVE
FLAPPER VALVE
.´•TH-385 THRV TH-436 HAS TWO
FILTERED HEATER FUEL PUMPS IN
SERIES WITH A HEATER SOLENOID
VALVE BETWEEN PUMPS AND
HEATER
Capacity,
(136 Gallons Usable, TH-385 thru TH-772 except TH-766).
8-7
FU EL R E TUR N
I
FUEL LINE
O
I
II 1’4HEATER
,FUEL
OISTRIBUTOR
ENGINE,
DRIVEN
PUMP
FUEL SU P ~LY
HEATER FUEL PUM P
WITH FUEL FILTER
VENT LINE
MECHANICAL CONNE CTOR
FIRE WA L L H
HEATER FUEL LINE
FROM LEFT FUEL
CELL ONLY
Is
1
r*t
FUE L LEVEL
SIGHT GAGE
FUEL SELECTORS
IDRP~IN
EDGE
IBAFFLED
CELL
X
eye CK VALV E
liiir
FILLER
CAP
c, FR OM RIGHT
FUEL CELL
FUEL)
SELECTOR
c
~Y
i~ sox SE6TION
Z;iniN
CELL:
-e
~N;I
CHECK
VALVE
I+
SIP~ON
BREAK
ENGINE
CROSS FE ED
LL~oRnlN
PRESSURE
RELIEF
VALVE
TO
RIGHT
AUXILIARY
FUEL PUMP
VENT
(HEATED)
L+*
TH-I THRU iH-384 ONLY
TH-I THR U TH-3 84 HAS TWO
FILTERED HEATER FUEL PUMPS
IN SERIES WITH A HEATER
50 LENOIC) V A LVE B ETW EEN
PUMPS AND HEATER
NOT APPLICABLE FOR TH-I
TH RU TH 3 8 4
ss-scu-rs
Figure
8-5, Fuel
System,
142 Gallon
Capacity,
(136 Gallons Usable, TC-1970, TC-2003 and after,
iE-1081, TE-1084 and after, TH-I thru TH-384, TH-766, TH-773 and after).
I FUEL RETURN
I
FUEL LINE
FUEL SUPPLY
1
II I~HEATER
.FUEL
~DISTRIBUTOR
ENGINE,
DRIVEN
sr
PUMP
U
FUEL PUM P
WITH FUEL FILTER
VENT LINE
FIREWP. LL H
FUEL LEVEL
SIGHT GAGE
FILLER CAP
1
I a
t
RESERVOIR
(F1NGER STRAINER)
~1
VENT
LINE
CHECK
VALVE
HE ATE R FUEL LINE
FROM LEFT FUEL
CELL ONLY
I
FUEL SELECTOR
VALVES
C
ii
TR*NSHITTERi
(BOTTOM
DGE CELL
LCECL
I
I
C~C
FROM RIGHT
~SFUEL CELL
I~Yr/ ‘434~
TO RIGHT
ENGINE
DRAIN
CROSSFEED
-e
TE-964 IH.U TL-10113 DO NOT
AUXILIARY
FUEL PUMP
HAVE FLAPPER VALVE
*~TE-938, TE-943 THRU TE-967 EXCEPT
;--DRAIN
PRESSURE
RELIEF
VALVE
SIPHON
BREAK
VENT
(HEATED)
8-6. Fuel System, 172 Gallon Capacity,
Gallons
Usable, TE-938, TE-943 thru TE-1 083
(166
Figure
except TE-1081).
8-8
TE -9 59 HA5 TWO FILTERED HEATER
FUEL PUMPS IN SERIES WITH A
HEA TER 50 LENO ID VALVE BETWEEN
PUMPS AND HEATER
FU EL RETURN
FUEL LINE
~FUEL
I
FUEL
DISTRIBUTOR
ENGINE,
SUPPLY
II
I’HEATER
DRIVEN
PUMP
1 VENT LINE
HEATER FU EL PUM P
W ITH FUEL FI LT ER
MECHANICAL CON N ECTOR
RESERVOIR
FI REWAL L
lu
I
FUEL LEVEL
SIGHT GAGE
F1 LLE R CA P
,(FINGER
STRAINER)
I El
I El/
FUEL LINE
FROM LEFT FUEL
CELL ON LY
FUEL SEL ECT ORS
I#eoaRo
ILEnDING
VENT
LINE
CHECK
VALVE
NG
CELL :i
EDGE CE LL:
MoT oa(I
CHECK VALVE
FROM RIGHT
FUEL CELL
SELECTOR
n´•-~::i´•lr
TO
RIGHT
ENGINE
i BOX SECTION CELL
CROSSFEED
PUMP
STRAINER
-ORAIN
PRESSURE
RELIEF
VALVE
SIPHON
BREAK
TH-432 THRU TH-772 DO NOT
HAVE FLAPPER VALVES
TH-385 THRU TH-436 HAS TWO
FILTERED H EA TE R FU EL PUM PS IN
SERIES WITH A HEATER SOLENOID
VA LVE BETWEEN PUM PS AND HEATER
VENT
[HEATED)
sa-sorla
Figure
8-7, Fuel
System,
172 Gallon
Capacity,
(166 Gallons Usable, TH-385 thru TH-772 except TH-766).
FUEL RETURN
~9 FUEL
I
LINE
ENG INE
DRIVEN
PUMP
FUEL SU PPLY
I
I VENT LINE
I
c
FUEL
D IS TR I BU TOR
ti
I
I
W
,HEATER FUEL PUMP
WITH FUEL FILTER
MECHANICAL CON N ECTOR
FIREWALL
LINE
CHECK
VALVE
g
LEVE L
SIGHT GAGE
i!.
ii!LtADIN(j
jI
i
*t*FUEL
FIL LER CAP
iii
ifilSMlri~i
(BbTtOM
iQiii
I
IY
I ~J
I
t
FUEL SEL ECTORS
~iDRA!N
ii:ji
EOOE
:I
liiBAFFLED
CELL:iii:
it
:r
HEATE R FUEL LI N E
FROM LEFT FUEL
CE LL ONLY
CH EC K VA LVE
~liiiiii
FROM RIGHT
FUEL CELL
iiil´•
SELECTOR
~iiSib:
:ii
FUEL PUMP
STRAINER
DRAIN
PRESSURE
RELIEF
VALVE
SIPHON
BREAK
*TH-I THRV TH-384 ON LY
1TH -1 TH RU TH 3 84 H A S TWO
FILTERED HEATER FUEL PUMPS IN
SERIES WITH A HEATER SOLENOID
BETWEEN PUMPS AND HEATER
ii/EXTERNAL
VENT
(HEATED)
ss´•ecu-lo
CROSSFEED
TO
RIGHT
ENGINE
NOT APPLICABLE FOR TH-I THRU TH-384
TOP MOUNTED TH-I THRU TH-384
Figure 8-8. Fuel System, 172 Gallon Capacity,
(166 Gallons Usable, TE-1 081, TE-1084 and after,
TH-1 thru TH-384, TH-766, TH-773 and
after).
8-9
FUEL RETURN
E~ FUEL
LINE
I
FUEL
DISfRIBUTOR
ENGINEDRIVEN
PUMP
FUEL SUPPLY
1 VENT LINE
II
I"HEATER
FUEL PUMP
WITH FUE L F I LT E R
MECHANICAL CONNECTOA
RESERVOIR
WING TIP
FUEL TAN K
1
FUEL LEVEL
SIGHT GAGE
.D RAIN
FILL ER CAP
EI
EDGE
TRANSMI TTE
E~D’""
aoGE
ceci~
R FUEL LINE
FROM LEFT FUEL
CELL ON LY
(FINGER
STRAINER)
FIREWALL
FUEL SELECTORS
/B’i~ig
(BOTTOM
I’
~p
I
CHE C K VALV E
FROM RIGHT
FUEL CELL
FUELI
I
SELE~TOR
TO
RIGHT
ENGINE
X
VENT
CINE
CHECK
VALVE
SECTION
C~ii
AUXILIARY
FUEL P UMP
CROSS FE E D
I-,
PRE~SSURE
SIP\H0N
RELIEF
VALVE
BREAK
II
VVENT
55-603-80
HEATED)
Figure 8-9. Fuel System, 200 Gallon Capacity,
(194 Gallons Usable. TH-6S9 thru TH-772 except TH-766).
FUEL RE TU R N
FUEL LINE
EN
FUEL SUPPLY
I
HEATER
DISTRIBUTOR
DRIVEN
PUMP
1 VENT LINE
I
MECHAN ICAL CONNE CTOR
I
HE ATE R FUE L LIN E
FROM LEFT FUEL
CELL ONLY
FIRE WP, LL
WING TIP
FUEL TANK
D
NG
EDGE CELL´•
iiiii
j
FUEL LEVEL
SIGHT GAGE
RAIN
FILLER CAP
t
FUEL SELECTORS
TRANSMI
i CLLL
1~
~lii%
:is
I,´•´•’
SMITTER
CHECK VALVE
FROM RIGHT
FUE L CELL
FUELI
iiiii~--1 I
SELE~TOR
iii
.ji
filiiox
VENS
LINE
i
SECTION
~a,,,
AUXILIARY
FUEL PUMP
CROSS FEE D
!i/
RIGHT
ENGINE
R
PRE~SSURE
SIP\H0N
RELIEF
VALVE
BREAK
II
VVENT
(HEATED)
Figure 8-10. Fuel System, 200Gallon Capacity,
(f 94 Gallons Usable, TH-766, TH-773 and after).
8-10
HEATER FUEL PUMP
W ITH FUEL F I LT E R
I
I
55-eos-al
RESERVOIR REMO VA L (TC- 1 608 ihru TC-2002, except TC- 1970; ~E-938, TE-943 thru TE- 1083 except
~E- 1 08 1; ~H-385 thlu TH-772, except TH- 766)
With the fuel selector valves in the OFF
position,
assu me
its
original shape.
d.
while
a.
Release the reservoir, al lo w i ng i t t o
c.
I
I nse rt t he connector
tilting both
bl y i n to t he reservoir
assem
the reserovoir and connector
assembly
upward.
drain the fuel cells.
line
b.
Re mo ve the
c.
Re move the
wing access cover and plate.
j ack pad cover plate.
L oo se n t he nipple clamp and disconnec t the
d.
to the connector assembly.
CA UTION
fue I
Care should be exercised
to
avoid
cross
thread-
ing the connector into the reservoir. Also avoid
bending or distorting the fuel strainer which is
NOTE
attac hed to the end of t he connec tor. for i t
may
become
Wrap the edges of the access hole and liner with
masking tape to prevent damage to the reservoir
during re moval,
Remove the connector
e.
voir while
tilting
assembly
from the
both the reservoir and connector
s
mall
Compress
the
re se rv o i r
s q ue ez e
reser-
assembly
by hand)
c i rcu m fe re nce
to remove from
and pas s i t t hrough t he fue I
the fuel cell.
Thread the
e.
until it will advance
foam inside the
reser-
into
access
a
ri ng
assembly into the reservoir
specific torque is re-
connector
further. No
no
quired.
f.
T i gh te n
g.
Connect the fuel line
h.
Remove the tape from the flapper valve and check
for fre e play and a good seal.
upward.
f.
enta ngl ed i n t he
voir.
the val v e
i
Check
the
to
nipple clamp.
make
to the c o nnec tor as se m b I y
the reservoir is
sure
positioned
properly on the bottom of the fuel cell.
Close al I ace es se s
j
FU EL CELI
4 O G A L.
CA UTION
The parts of the aerobatic reservoir type fuel
cells, baffled fuel cells, and non-baffled fuel
cells are not interchangable. When installing a
A
FUSELAGE
FUEL IINE
sis Y
I
CTO5
A5Sr.
~FUEL
F1N GER STRAI~E R)
Tit;
type of reservoir fuel cells and does NOT
airplanes are NOT certified for aerobatic
flight; refer to the applicable Pilot’s Operating
Manual for certified flight operations.
8-11. Fuel Cell
ron
Reservoir, (TC-1 608
TC-2002, except iC-l 970; TE-938,
TE-943 thru TE-1083, except TE-1 08 t
TH-385 th ru TH 772, except TH -766)
thru
REMO I/ING MA lN FUEL CEL LS
RESERVOIR INSTALL4 TION (TC- 1608 thru TC-2002,
except T%- 1970; TE-S~B, ~E-943 thru TE- 1083 ex-
a"d TE- I thru
a.
cept TE-1081, TN-385 thru TH-772, except TH- 766)
b.
adapter
Install the reservoir after the fuel cell is in the
complished
access
as
plate
wing
is installed. Installation may be
ex-
press or imply that the airplanes involved are to
be flown in an aerobatic configuration. The Ba-
55 -295-5
before the
use
particular installation. The reference to ’’aerobatic" in this "CAUTION" refers only to the
RESERV OIR 6,
C O N N E CT OR ASSY
FOR EASIER INSTAL-
Figure
fuel ceil,
only those items pertaining to
being installed. Extreme care
should be used when installing the finger fuel
strainer to prevent damage to the fuel ceil. The
long finger fuel strainer (approximately 9 inches)
is used only in the aerobatic reservoir type fuel
cell as provided in Kit No. 35-9012. AH other
inboard main fuel cells that use a finger fuel
strainer use the short´• type finger fuel strainer
(approximately 4 inches long). Refer to the applicable BEECHCRAFT Parts Catalog for the
new
that particular cell
R E5E R VOIR
and
ac-
Remove the transmitter, the liner
c.
d:
thru ~C- 1607
Drain and purge the fuel cell.
Re move the access plate at the fuel cell filler cap
and transmitter.
inboard fuel ceil
follows:
(7~C-1
TE-942, except TE-938)
plate.
the j ac k pad
access cover
and
cover
Remove
cover
plate
and
remove
the
fuel st rainer.
a.
I i ng the
b.
smal I
Tape
t he
reservoir
flapper
valve
s hut
before ins rat
rese rvoi r.
Compress
c i re umfe re nc e
into the fuel cell.
the
(sq ueeze by hand) i n to a
it through the fuel access ring
re servoir
and pass
e.
Remove the fuel cell drain
f.
Remove the fuel cell
of the
plug.
door
on
the underside
wing.
g.
door
access
on
Disconnect the fuel cell
the underside of the
wing
plumbing
at
the
access
at the outboard end.
8-11
N6TE
Wrap the edges of the access hole and liner
masking tape to prevent damage to the cell
ing removal.
INS TA LL ING A UXIL IAR Y FUEL CELLS (TC- I thru
TC- 1607 and TE- I fhru TE-942, except ~E-938)
with
durNOTE
For
h.
U nsnap the fuel cell and
remove
it from the
wing
ease
of installation,
place
where the temperature is
allow a sufficient heat soak
area
cavity
flexibility
INS7-~LLING MA lN FUEL CELLS (TC- 1 thru ~C- 1607
and TE- 1 thru TE-942, except ;rE-938)
at
an
i eas t hOO F and
period
to
e ns ure
of the fuel cell.
insert the fuel cell
Carefully
a.
the fuel cell in
through the
access
hole and snap the cell in place.
b.
Install the drain valve tube in the inboard aft
N OT E
corner
of the fuel cell.
Connect the plumbing
c.
For
ease u I
i ns tal I at ion. p lace t he fuel c ell i n an
where the temperature is at least hO"F and
area
allow
sufficient heat soak period
fle xibi ii ty of the fuel cell.
a
to
d.
Install the fuel cell
fuel cell
en sure
access
plates
Carefully
a nd
b.
on
u
nde rs i de of the
plumbing
I ns tal I t he t rans mi t ter.
f.
Install the
to
clamps
I I
Inst all the
g.
I
c
on
at the access
hole
plug,
b.
remove
t
t he
i nch-pou nds
Good year
c
Remove the fuel cell
wing
and
remove
c el
through
on
Is.
e.
corner
the
access
inspection
plates
the fuel ceil
Disconnect the plumbing
board ends of the fuel cell.
at
5 i nch- pou nd s
on
access
the
u
nder-
the inboard and out-
w i ng.
A pp i y
adapter
clamps on t he i ntercon nects. Torque
r I inch-pounds on Uniroyal and ?5
Goodyear cells.
11
access co vers.
se iec tor
valve s i n t he O F F pos i tion. drai n
cells.
in this section.
Remove the
c.
top of the wing)
access cover
and transmitter (inboard
desc r i bed i n FU E L C E L L TRANSM ITT E R R E M O V A L i n this section.
d.
as
Remove the exhaust heat shield and the
cover on
the underside of the
e.
Remove the fuel cell
f.
Remove the
cotter
access
wing.
access
pin
plate.
which holds the
flapper
valve inside the inboard interconnect tube if installed.
Disconnect the inboclrd and ou tboard i nterconnect
g.
through the access doors.
Airplane serials TH-I
thru TH-384. TH-7hh. TH773 and after, TC-1970, TC-’003 and after and TE- 108 I.
TE- 1084 and after:
with
dur-
ing removal.
I
through
8-12
to the
between the
h.
Wrap the edges of the access hole and liner
masking tape to prevent damage to the cell
the fuel cell and
adapter
Sealing Chart)
b.
Remove the access cover and the transmitter (outboard in top of the wing) and fuel level sight gage if installed.
a s des cr i be d i n FUEL CELL TRANSMITTER REMOVA
L
plates.
Remove the drain valve tube from the inboard aft
of the fuel cell.
Unsnap
on
Wi th the
wing
tu bes
f.
to
I ns tal I the
a.
the
door
NOTE
cavity.
the in-
~9EMO VING INBOARD. LEADING EDGE FUEL CELL
(TC- 1608 and after, ;TE-938, TE-943 and after and
TrH- I and after)
on
d.
through
Torq ue
U niroyal cells
access covers.
inboard transmitter is accessible
in the uppe r nace I I e s ki n.
wing.
i n tercon ne c t s
Drain and purge the fuel cell,
Detach the fuel cell cap adapter from the wing and
the inboard and outboard fuel cell transmitters. The
side of the
I n s t al I t he
nipple clamps
h.
on
located under the
and skin attach.
the
REMO V/NG A UXIL /A R Y FUEL CELLS (TC- I fhlu
TC- 1607 AND
thru ~E-942, except TE-938)
a.
Install the fuel cell cap
g.
d.
5 i nc h- pou nds
f.
access
wing.
e.
nipple clamps
the
plates,
upper nacelle skin.
Permatex No. 2 (Item 3.
Install the fuel cell drain
I nstall the Fuel st rai ner.
and ~5
through
place.
Connect the fuel cell
the
c.
the
insert the fuel cell
snap t he cell in
access
the underside of the
The inboard transmitter is accessible
spection door in the
a.
on
Install the inboard and outboard fuel cell transmit-
e.
ters.
hole
the inboarct and outward
at
ends of the fuel cell.
remove
it from the
Disconnect the hose to the sump
access door.
asse
mbl y
the inboard
wing
Remove the hose, sump
fuel outlet.
assembly
and the
3.
Disconnect
the
heater
fuel
line
(LH
cell
only).
c.
Connect the
d.
Airplane
773 and af ter
i.
Airplane serials
TC- 1608
TC-2007, except
TC- 1970: TE-938. TE-943 thru TE- 1083, except TE-1081:
thru
TH-385 thru TH-772, except TH-766:
I
Remove fuel cell reservoir and fuel
tor
described in RESERVOIR REMOVAL in this section.
as
TC 1 970
lines.
TH 1 t h ru T H 3 84. TH -766, 7’ H
TC- 2003 and after and T E 1 08 1
TE-1084 and after:
I.
connec-
vent
se ri al s
ve
le ro
pi I e
Position the fuel ceil in
and hook toge t her pre s s i ng
Di scon nect t he vent lines at the outboard
e
nd of
the cell,
as
described
the velc ro ta pe.
in
IN-
SPECTION OF MAIN F U E L C E L L FLA P P E R V A L V E i n
this section.
k.
Snap
outboard
press the
area of
ward i n t he
Inspect flapper valve
j.
place and
ou t
out the
cell and
pull
it
through
the top of the
3.
ope ning.
access
4.
serials TC- 1608
Airplane
e.
NOTE
Install hose, sump asse mbl y and fuel outlet.
1 nstal I heate r fu e I I i ne L H only
TC 1 970: T E -93 8
TC-2002. except
TE-943 thru TE- 1 083
except T E 108 1
TH-385 thru TH-777_. except TH-7hh:
t he edges of the access hole and the liner
masking tape to prevent snagging the fuel
during its removal.
Wrap
with
cell
I
I ns t at I the fu e 1
II
and fue I
reser vo i r
c o n nec
heading RESE R-
VOIR INSTALL ATION
CA UTION
INSTALLING INBOARD LEADING EDGE FUEL CELL
(TC-1608 and after, ~E-938, TE-943 and after and
TH- 1 and
ce
described in this section under the
tor as
after)
This caution does not
apply
airplanes
to
TH-I thru TH-384. To prevent pushing the inter
con nect tu bes out of place when installing the
i nboard le ad i ng
N OT E
sary to
in the bo x
This note does not
apply to airplane serials TH- 1
installing a new inboard
leading edge fuel ceil, particular attention should
be paid to the removable yellow tag which is
attached to the cell near the nipple and which
edge fuel cell,
hol d i nt ercon nec t
~ec t
it may be
neces-
through
access
t u bes
ion cell.
tfiru TH-j84. Prior to
reads
as
TH 1S
f.
Connect the fuel outlet. Torque 30 to .70 inch
pounds and safety wire.
Install the clamps on the interconnect tubes. Torg.
I i nc h- po u nd s on U niroyal
que the nipple clamps to i I
cells and 25 r 5 inch-pounds on Good y ear c el I s.
follows:
CELL
CONTAINS
AN
i NTE R N A L
NIPPLE WHICH IS COVERED BY A WEB
INTEGRA
L
WITH THE CELL. WH EN ~HIS
NOTE
CELLIS B EING 1N STA LL E D I N M OD E L S
E55
AND 58
EQUIPPED
WITH THE OUT-
LOCATED ON THE OUTBOARD END, 2.87
airplane serials prior to TC- 1654. TE-~6J and
were originally equipped with inboard interconnect flapper valves, there is no
need to replace a flapper valve should either one
I NC H E S FORWARD OF TH E LOWER A FT
or
BO ARD LEADING E DC E C E L L, TH E NIP-
On
PLE M U ST 8 E LOC AT E D A N D T H E W E B
TH-332 which
CA REFULLY CUT-OUT, THIS NIPPLE IS
both be removed.
CORNER.
N OT E
h.
Install the fuel cell
i
Install
heading
For
ease
of installation,
place
the fuel cell in
an
plates
as
and
safety
wire.
described under the
FUEL CELL TRANSMITTER IN STALL ATION
in this section.
j.
where the temperature is at least 600F, and
allow a sufficient heat soak period to ensure
area
flexibility
access
transmitters
the
Install the
access covers.
of the cell.
REMO VING BOX SEC TION CELL (TC- 1 608 and afTE-938, TE-943 and after and TH- I and after)
Install the cell th rou gh the top outboard
a.
access
opening.
b.
upper
a.
Align
hangers
wing and fasten it
place.
the snap
that
secure
the cell to the
all
With the selector valves in the OFF position. drain
wing cells.
b.
~Remove
the
screws
securing
the fuel cell filler cap
8-13
adapter
or access cover
on
to the
wing skin.
b.
Re move the inboard and outboard
c.
Remove the
wing
covers
to
Remove the inboard and outboard fuel cell
access
de scribed
the underside of the
d.
the
access
wing.
Remove the
c.
plates.
screws
securing the filler
adapter
cap
skin.
access
and the transmitter
cover
as
the head i ng F U El, C E L L TRA N S M ITT E R
u nder
REMOVAL in this section.
clamps.
Remove the interconnect
e.
Remove the inboard and outboard
d.
on
e.
CA UTION
covers
Remove the inboard and outboard fuel cell
access
wing.
plates.
f.
Airplane serials
access
the underside of the
TH-I thru TH-234 do not
apply
Disconnect the
The vent lints
this caution. When removing fuel cells from
the interconnect tubes, exercise caution to preto
are
Snap
g.
1 ines and inte rcon nect tubes.
vent
located aft,
out
near
the cell and
the outboard end.
pull
through the
it
access
opening.
vent pu I I i ng i n te re on nec t tubes out of the in
board andior outboard leading edge cells.
NOTE
f.
g.
acces s
Disconnect the drain and vent plu mbing.
Snap out the ceil and pull it through the outboard
open ing.
Wrap
edges of
the
liner with
ceI
mas k i
I d u ri ng i t s
opening and
s nagging
access
the
t he
remo vai
OUTBOA RD LEADING EDGE CELL
and after and TH- I and after)
INS TALLING
NOTE
the
ng tape t o p re ve nt
(TE-938, ~E-943
Wrap the edges of the access hole and the liner
with masking tape to prevent damage to the cell
during its removal.
NOTE
For
place the fuel
cell in
an
following portion of
applicable on airplane serials
TH- I thru TH-384. Prior to installing a new outboard leading edge fuel cell. particular attention
should be paid to the removable yellow tag
which is attached to the cell, near the nipple.
Ful´• ease of installation, place the fuel cell in an
area where the temperature is at I east 600 f: and
to r:n~ul´•e
of installation,
area
NOTE
allow sufficient heat soak prl´•iocl
bility of the fuel cell.
ease
where the temperature is at least hOOF, and
allow a sufficient heat soak period to ensure
INSTALLING BOX SEC TION CELL (TC- 1608 and after,
TE-938, TE-943 and after, and TH- I and after)
flexibility
of the cell. The
this
is not
note
flexi-
Collapse the cell and install it through the out
opening.
b.
Align the snap hangers that secure the cell to the
upper wing skin and fasten it in place.
a.
board
adapt e 1´• or Lic cc ss plate to the
inch-pounds and safety wire.
2(ltem 3, Sealing Chart) between the
Install the fi I ]e r
a.
fuel cell.
Torque
Apply Permatex
adapter and skin
Install
b.
45
No.
ca p
55
to
and attach.
the
the
outboard
access
ope ni ng,
c.
upper
Align the snap hangers that secuie the cell
wing skin and fasten it in place.
d.
C on nec(
e.
Install
clamps
Toryue the nipple clamp
cells and 2.5
g.
on
1
I I
pounds
Install the fuel cell
f.
Install the
ada pee r
.5 inch
to
the
and drain lines.
t he vent
the
on
the
interconnect
inch
on
G ood year
access
plates
tubes.
U ni ro y al
securing the
t he wing skin.
screws
or ac cess c over
to
and
safety
TION in this section.
f.
With the selector val ve s i n t he O F F
wing cells.
8-14
I nstall the
access
covers.
(TE-
REl41C, VING THE FUEL SELECTOR VA L VES (TC- I
thru TC-2002, except TC- 1970,
thru TE- 1084,
except TE- 108 1)
a.
Turn both fuel selector valves to OFF.
b.
U ns nap t he floor mat andremove the
curing the fuel
c.
the
vent lines.
clamps on the interconnect tubes. TorI inch-pou nds on Uniroyal
clue the nipple clamps to 11
cells and ’.5
5 inch-pounds on Goodyear cells.
Install the cell access plates and the transmitter
e.
and safety wire. install the transmitter as described under
the heading FU E L CELL TRA N S MITT E R I N STA L LAInstall the
wire.
fuel ceil filler cap
REMOVING OUTBOARD LEADING EDGE CELL
and after and T~H- I and after)
938
a.
Connect the
ce I I s.
access cover.
Install the
c.
d.
through
cell
access
positio n, drai n
certain
d.
selector valve
W he n
re mo v i ng t he
phone jac ks,
screws se
cover.
fu e I
se ie c t or v al ve
etc., if instal led,
With the fuel drained,
are
cover, be
disconnected.
identify the
fuel selector
valve
plumbing
and
INS TA LL ING
and disconnect.
Remove the fuel selector valve
e.
remove
attaching
screws
Lubricate
a.
I
the
fuel
line
threads
Position the selector valve
b.
rl
oy
7
et
and install the
-ce
on
under the
SELECTOR
/h
I
I
the
mounting bruck-
plu mbing.
Install the fuel selector control cable
d.
FUEL
O
s
anti-seize
attaching bolts.
Install the fuel selector valve
TO
0~
with
be fo re i n s t at la t i o n
i
o
(TC-
co mpou nd (See Table of Thread L u brican t s i n Section 7,)
/-C
1
SELECTOR VA L 1/E
after)
and TH- I and
the fuel selector valve.
CROSS FE ED
2
THE FUEL
1970, TC-2003 and alter, TE- 1 08 1, TE- 1084 and after
heading
as
described
F U E L S E L ECTO R V A L V E C O NT RO L
CABLERIGGING in this section.
PANE L
ON-
FUEL SELECTOR VA L VE CONTROL CABLE REMO 1/A L (TC- 1970, TC-2003 and after, 7-~- 1 08 1, TE1084 and after, TH- I and after)(Figure 8-1’)
Remove
a.
OFF
FUE L SELECTOR VALVE
(L.
Shown,
H,
cover
o v ert ra ve I
plate,
tu be
and slider
(held by snap-ring) from selector valve gear box (iocated in
wheel well).
Cover Plate
i, Stop Sc rew
Rotate selector handle pointe r i n fuel panel) to
position, rotate cable tin wheel well) by hand until
cable is disengaged from fuel selector panel.
Slide cable out of housing and fuel selector valve
c.
b.
Removed)
OFF
6,
Slider
2.
Over Travel Tube
7.
Cable
3.
Selector Valve Gearbox
8.
Cross Feed Port
4.
Selector Gear
9.
Over T ravel Po rt
5.
ControlC able
Housing
gear bo x
Figure 8-1 2. Fuel Se lector Valve, (TH-1 and after,
TC-19 70, TC-2003 and after. TE-1081, TE-1084
and after).
1 in.
INSTALLING THE FUEL SELECTOR VA L I/ES (TC-I
ihru TC-2002, except TC- 1970, TE- 1 thru TE- 1 084
except TE-I 08 1)
a.
Position the fuel selector valve and make certain
the selector valve shafts
removed and
b
c.
are
installed in the
properly engaged
same
position
as
same
plumbing identity tags.
If equipped,
d.
selector valve
I ocalion
as
I
in, DIAhl,
re mo ved.
when
1/----APPROX.
in. LONG
phone jacks,
etc.,
on
fuel
cover.
Install the fuel selector valve
cover
and
1/8
in.
Re mo v e
Figure
install
1/4
with the ´•:´•alves.
Install the fuel selector val~a attaching screws.
I ns tall t he fue I se lec tor v at ve pi u mbi ng, be ing ce r-
tain it is in the
e.
are
8-13.
Rigging Tool, (TH-1
and after,
TC-1 970, TC-2003 and after, TE-1081, TE-1084
and after).
attaching
acre ws.
REMO VING THE FUEL SELECTOR VA L VE (TC1970, TC-2003 and after, TE- 1 08 1, TE- 1084 and after
and
and after)
a.
b.
Drain the fuel system.
Place the airplane on jacks and
partially
retract the
gear until the inboard main gear door is full y e:xte nded.
c.
Remove the selector control cable
this section under the
heading
as
described in
FUEL SELECTOR VALVE
CA UTION
Handle cable with
care to
prevent da mage.
FUEL SELECTOR VA L VE CONTROL CABLE lNS TALLA T70N AND RIGGING (TC- 1 970, TC-2003 and
after TE- 1 08 1, TE- 1084 and after, TH- I and after)
(Figures
8- I’, and 8-13)
CON TROL CABLE REMOVAL.
the
d.
Remove the fuel selector valve
e.
Remove the bolts
mou
nti ng bracket,
securing
plumbing.
the selector valve to
To aid in the
rigging procedure, a locally manufactured
"Rigging Tool’ (see Figure 8- 1 f) ma y be constructed for
turning the selector gear. Tubing of 1/4 or 3/8 inch diameter
8-15
is used for the handle and 1/8 inch steel
protrusions which
pins
are
used for the
contact the selector gear,
With fuel selector control pane I assembly ins tailed, cable
housing routed through the structure and the fuel valve
installed in wheel well, proceed as follows:
Remove
a.
cover
plate,
overtravel tube and slide
(held by retaining ring) from selector valve
gear box
The fue I
quantity circuit for the inboard leading edge fuel
eel I must be reconnected whenever the original fuel le vel
transmitters are replaced. The required circuit connections
are provided in Figure 8-15, and are also included in Kit
55-5001 (which is furnished with the purchase of the
replace-
transmitters). The circuit changes consist of reconnecting the wires in a single wing fuel quantity indicating system
using the existing fuel gage and existing wires.
ment
(located
in wheel well).
b.
Set selector valve (using: spanner wrench or rigging toolf to CROSSFEED position (arrow on selector gear
at 12 o’clock).
Insert
c.
cable
through
overtravel
through the gear box and cable housing.
slides freely with no hang-ups,
d.
pbrt and slide
Be certain the cable
Slide cable inboard until the inboard end makes
selector. The outboard end of the cable
AD~USTING FUEL QUANTIN INDICA TOR (TC- I
TC- 1607, TE- I thru TE-942, except
TE-938)
The fue I q uanti ty system may be adj u st ed by removing the
liquidometer access covers fro m the cells and bendi ng t he
float wire up or down slightly to obtain the
proper reading in
both the full and empty tank conditions.
contact with gear in
should be
approximately
4 inches from the gear box surface.
Set selector handle
e.
pointer (located in the fuel
position (pointing inboard).
selector panel) to CROSSFEED
Hold in position.
f.
NOTE
Rotate cable (LH threads) until tip end of cable is
max. from gear box surface,
Install slider and secure with retaining ring (re-
Do not raise the outboard float in the
2.8" min. to 3.2"
cell
g.
moved in step
C yde
proper
h.
is
install overtravel tube (removed in step
the selector handle to all positions and check for
to
Install and
j.
Do not
safety
apply
wire
grease
or
cover
plate
on
40
gallon main
auxiliary
cell when the i nboard float
the bottom of the cell and power is applied
reverse the power leads to
the circuit. Never
the 25
operation and selection.
Safety wire the overtravel tube.
i.
or
gallon
tions will
main
cause
ce II
trans m itte r. These
ac-
excessive current flow in the
circuit.
Airplanes TC-113, TC-129, TC-133, TC141, TC-148, TC-164, TC-166, TC-168 through
TC 1607, TE- I through. TE-942 except TE -93 8,
screws.
oil to gear.
and
prior airplanes incorporating Service Letter
No. 4 have two 50 ohm resistors to protect the
system components. Two fu se s are installed to
INS TALLA TION OF f7EPL1CEMENT FUEL LEVEL
TRANSMITTERS IN THE MA /N FUEL CELLS (TC-I
thru TC- 1607, TE- I thru TE-942, excepl
protect the system on airplanes TC-I,TC-2, and
TC-34 through TC-167, except TC-113, TC-129,
TC-133, TC-141, TC-148, TC-164, TC-166 and
The fuel level transmitters, P/N 95-380012-1 and 95-380012-
airplanes modified ac cordi ng to Service Letter
No 4. Airplanes serials TC-3 through TC-33 not
modified according to Service Letter No,4 have
no circuit protection other than the 5
amp circuit
breaker. On these airplanes, exces sive current
3,
originally installed in the inboard leading edge (main) fuel
cell on these airplane serials are not available for
spares
replacement. The transmitters that are available are not of
the same manufacturer, and are not comparable in the same
wing indicating system as transmitters which were originally
installed in the airplane. Thus, when replacement of either
transmitter is
same
required, both transmitters installed
cell must be of the
may burn out the fuel level transmitter.
in the
manufacturer. After the initial
of both transmitters and the accomplishment of
same
replacement
the required rewiring, the transmitters may be replaced
vidually as required for maintenance of the airplane.
indi-
FUEL CELL rril4NSMITTER REMO VA L
The current fuel level sensor which should be used as a
r e p I ac e m e n t f o r t h e i n b o at d tT a n s m i tt e r i s P/N 9 5 3 8 00 2
1
1 3.
This unit supersedes P/N 95-380012-5 and is a replacement
for P/N 95-380012-1. A servicable transmitter, PM 95-
CA UTION
Make
sure
battery
connected from
and
ex te mal
power
are
dis-
airplane.
380012-5, which has
been previously installed as a replacement, and which is stamped with the manufacturers P/N
7740-56, may be reused. The current fuel level sensor which
should be used as a replacement for the outboard transmitter
is PM 95-380012-15, This transmitter supersedes P/N 95380012-7 and is a replacement for P~ 95-380012-3. A servic-
able transmitter, PM 95-380012-7, which has been previous-i
ly installed as a replacement, and which is stamped with the
manufacturers PM 7740-55, may be reused.
&16
b.
Remove the access cover over the transmitter.
Disconnect the electrical leads from the transmit-
c.
Remove the
a.
ter.
screws
securing
the transmitter to the
fuel cell.
d.
avoid
Remove the transmitter from the cell. Use
the float wire.
bending
care
to
BUS
EXISTING INBOARD
EXISTING OUTBOARD
(95-380012-1)
(95-3 80012-3)
#2 STUD
%4 CONN.
STUD
FU LL
42 STUD
#3 STUD
nl STUD
SC1 STUD
DASH UNIT
43 STUD
JUMPER WIRE IS
NOT INSTALLED ON
ALL AIRC RA FT
5 5-36 9-265
Figure
8-1 4.
Wiring Diagram, (Original Transm itters)
BUS
95-380012-1 5
95-380012-1 3
(INBOARD TRANSMITTER)
iY2 STUD
42
DASH UNIT
(OUTBOARD
TRANSMITTE R)
FULL
EMPTY
44 STUD
STUD
STUD
nl STUD
INSULATED
CASE
ATTACH TO
MOUNTING SCREW
GROUNDED
CASE
55-369-264
Figure
8-15.
Wiring Diagram, (Replacement´• ~inboard and outboard transmitters)
&17
NOTE
if
Before installing the transmitter, inspect
liner material is grommet or felt. If grommet.
replace as required. If felt is replaced, fold a
I/Z x 1/16 inch strip of felt around the edge of
opening in the liner and
(Item 2, Sealing Chart).
the
I N D IC ATI NG
M AINTENANCE
FUEL FL OW INDICA TGF
(TC-2276, TC-2363 and after,
7~1H- 1199 and after)
~E- 1183 and after
FU EL FLOW
PRACTICES
/NSTALLA TION
FUEL CELL
The fuel flow indicator is
an
aid
The
engines during flight.
the
to the pilot when leaning
major components of the
the indicator.
system are the transducer or transmitter and
The transducer or transmitter is located in the fuel line of
each engine forward of the firewall, This de v ice gene rates
that is directed to the fuel flow indicator. The fuel
a
cement with sealer
signal
Position the transmitter in the fuel cell.
Make sure the float arm is mechanically
a.
b.
flow i ndicator
free
through its full range of travel. Non-metallic floats must
turn freely on the float arm.
Install and torque the retaining screws to ’5
c.
and
inch-pounds
safety
pointers,
after)
left
a.
Open the tight engine cowi.
b.
Di
s connec
t
t
connection,
Disconnect
c.
he
the
adjusting the fuel quantity
register a ’F’’ (fu II) reading, make
the fuel cells are completely full.
When
of
sure
br acket
to
gages
fuel
the
lines
Calibrate the fuel quantity gage
Ensure that the fu e I
e.
ceiIs
as
corresponding
to
full.
gage being calibrated are
Turn the calibration screw in back of the
printed ci re u i t board until the needle on the
the "F" (full) mark.
glareshield
fuel
u nsc re w i ng
w
i ri
as
or
n
i ines
at
g
from
t
he
the
t he nu t s secu ri ng
transmitter. Cover the
from
or
the
transmitter
clamps.
two
two
the
to
clamps
mounting
Remove
the
transm itter.
a.
Position the transducer
or
transmitter in place
with
secure
the
two
on
clamps.
c.
U ncap and rec on nec t t he t wo fuel lines.
C on nec t t he e lec t rical w iri ng at the connection.
d.
Close the
b.
engine
cowl.
follows:
quantity
Rein stall the
remove
or
mounting bracket and
Safety wire the clamps.
circuit board.
to
t ricai
prevent contaminants
to
the
Locate the two printed circuit boards on the
b.
back of t he i ns t ru ment pane I j u st to the ’left of center.
Loca te t he calibration screw in the back of each
c.
corresponding
fuel quantity gage points
ec
TRANSDUCEA OR TRANSMITTER INSTALLATION
outli ned in Section 3
as
and
transducer
that
u nder GLA R ES H IELD RE MOV A L.
the fue I
I
two
transmitter by
or
securing the transducer
glareshield
e
entering the fuel lines.
Cut the safety wire from the
d.
NOTE
1
per hour.
engine, and
the engine
subpanel.
ends
d.
eac h
located
the fuel lines to the transducer
ADJUSTMENT FOR FULL READING
printed
for
in the upper RH corner of
The circuit breaker is located in the
cluster.
instruments
is
transducer
Remove the
one
TRANSDUCER OR TRANSMITTER REMOVAL
ADJUSTING FUEL QUANTIN GAGES (TC- 1608
and after, TE-9~8, TE-943 and alter, and TH- 1 and
a.
gallons of fuel
readout in
a
wire.
Connect the electrical leads to the transmitter.
d.
gives
The indicator has dual
outlined in Section 3
under GLA R E SH I E LD INSTALLATION.
ADJUSTMENT FOR EMPP(R EADING
INS TALLA TION OF VELCRO TAPE (KIT NO. 359009-55) WITH REPLA CEMENT FUEL CELLS (TCI thru TC- 1298, TE- I 1Ylru TE-767)
Airplanes that have had or will have existing fuel cells
replaced with spare baffled type fuel cells (P/N 35-38013535-380135-2, 35-380135-3, and 35-380135-4) should install
Kit 35-9009-5S in the fuel cell liner top, bottom, root rib
and spar as described below. Serials TC- 1?99 and after
and TE-768 and after
the
quantity gages can be adjusted to register an "E"
position by carefully bending the float arms of the
inboard fuel quantity transmitters. The fuel gages should
read i´•E" (empty) with th ree (3) gallons of unusable fuel
equivalent of
are
delivered from the factory with
Kit 35-9009-5S in stalled.
The fuel
(em pty)
aboard.
8-18
a.
under
Remove the fuel cell
the
heading
as
described in this
REM OVING
AND
section
IN STALLIEJG
MAIN CELLS.
E3
AC CE SS
NOTE
cell.
the fuel
of
complete removal
covers
I
that have had any of t he preceding
previously installed do not require
Airplanes
fuel cells
P P EN ING
V E LC
RP
TA P E
Access
and inboard fitt i ngs should be removed
ana the inboard end of the fuel cell pulled
installation of the
back far enough to allow
velcro tape.
bonded to
as
Ehown
1 8,
EDGE FUEL CELL
\s.7"
by dipping into methyl ethyl
Activate the velcro
an d
I re m 19, Consumable Materials Chart)
ke to ne
mso*aoir*olNG
Co n s u m ab I e
Chart).
~Iaterials
c.
It e m
naphtha,
with
surface
sanded
ii
the surf ace that the velcro tape will
in Figure 8-16 and cienn thr
Light ly sand
b.
be
the velcro tape in place as shown in Figure 8-16.
Position the fuel cell in place and press the
d.
velcro pile and hook t oget he r by pressing outward in the
area
of the velcro tape.
Inspect the flapper
it’s
under
own
INSPE CTION
weight.
If the
MAIN
OF
free
for
valve
e.
CELL
33-36-1
Figure 8-16, Installation ot Velcro TaFe,
(TC-1 thru TC-1 298, TE-1 thru TE-767).
movement
valve binds,
flapper
FUEL
:2.5"
press
see
FLAPPER
outboard of the
V ALV E in this section.
fuselage
on
the upper skin
cne h
u
u´•ing
leading edge.
NOTE
NOTE
Before
for any
closing the zipper, inspect
foreign material.
the fuel cell
On
airplane
cell
access
outboard
f.
Close the
zipper
and refer
to
REMOVING hND
serials TH-1 thru TH-384 the fuel
plate is circular and located just
of the fuselage on the lower skin of
wing leading edgz.
each
INSTALLING THE MAIN CELLS in this section for
f u rt he r i n s t ru c t i ons
installing the fuel cell.
on
c.
safety
Cut the
from the fuel cell
wire and
access
remove
the
attnching
bolts
plate.
NOTE
NOTE
Installation of Kit 35-9009-SS (velcro tape) is
required on a first time basis only for each
fuel cell.
Repeat installations of the kit
unnecessary when
ne w
fuel cell s
are
Clean the
are
re movi n_E
installed,
d.
INSPECTION OF 7HE BAFFLE MAIN FUEL CELL
FLA PPER
VAL VE
VA L VE OR RESER VOIR FLA PPER
zipper
e.
area
the
airplanes
or
fuel
cell
that
are
equipped
with baffled main fuel cells
flapper valves should be
recommends that
Aircraft
(Beech
reservoirs,
the
inspected periodically
the inspection be accomplished at each ann ual inspection)
for freedom of operation and proper seat ing.
The i ns pect ion may be
E10
accomplished
a.
Drain all fuel from the
b.
Remove the
reranguiar
as
follows:
airplane.
access cover
located just
access
plate
before
Remove the fuel cell
access
plate
and open the
in the baffle of the main fuel cell.
Locate the
section of the baffle
On
around the
plate.
flapper
or
valve in the lower outboard
reservoir and determine if the
valve is metal or phenolic.
If the flapper valve is metal, it should be
f.
and
repaired,
if necessary,
as
flnpper
inspected
described below.
flapper element of the valve thro uch
no binding and the element
should seat sec urei v again st the vnlve plate.
If the I´•lappe r ele me n t b i nds and/or does not
seat properly, the flap per element arm could be bent. The arm
can be straightened by placing a screwdriver between the arm
1
Move the
its full travel. There should be
a-18A
and the element and
pressing
the elsme~lt toward the closed
position.
3.
If after
valve must be
the arm, the
properly, the
not seat
napper
valve i,
phenolic,
and reworked, if necessa~,
1
Move the
t
flapper
fu 11 trave I. There should be
s ho u id se at
securely
2.
flapper
flapper
remo ved.
If the
g.
inspected
straightening
and/or does
element still binds
If the
no
as
i
it should be
II
described below.
I
i ts
I
valve element
through
I
1/
I
\41
binding and the element
agil inst the valve plate,
element binds and/or does
flapper
i--;
not
~Li
properly, the upper rear side of the flapper element may
be binding against the valve plate.
The flapper valve element may be relieved
3.
from binding by filing a small radius on the upper rear side of
sent
Figure
the element.
lo´•
\r
8-17. Fuel Vent Line
NOTE
shop towe 1
placed directly
A
the
light oil may be
flapper valve to absorb
saturated with
below the
du st durin g rework.
phenolic
configuration would create a negative pressure that would
pull the air, or air and fuel from the fuel cell. At serials TC- IhUY
other
and after: TE-9j8, TE-94j and after; and TH- 1 and after, the
electrically heated to protect it from icina
major components of the system are the
5-amp circuit breaker in the left subpanel and the heater
wrapped around the exposed portion of the vent. The resistance
e?ttemal vent tube is
conditions. The two
After determining that the flapper valve is
it.
functioning properly, thoroughly wipe the area in the vicinity
of the flLlpper valve with an oil saturated shop towel.
of the heater at
room
27.88 ohms for
h.
Clean the easket
contact area
on
i.
temperature should be between 1s.7~ and
delivery of 37.5
watts at
25 volts.
tile fuel cell and
plate.
zipper in the baffle.
install a new gasket, and secure the fuel cell access
j.
plate in place.
k.
Tighten the fuel cell access plate attaching bolts to
a torque of 43; to 50 inch-pounds and safety wire.
Reinstall the access plate on the wing leadiIlg edge
i.
fuel cell
a
access
Close the
skin.
INSTA LLA TION OF FUEL FLARED FITT~NGS
installing flared fittings and hoses, make sun the
are lubricated properly isee Figure 2-3j with
anti-seize compound tin accordance with the TAB LE OF
THREAD LUBRICANTS). When previously installed
fittings are removed, they should be wiped clean and
relubricated be fore they are rei nstnlled. Torqu e all fitt ings in
When
threads
EXTERNA L FUEL CELL VENT LINE
accordance with th e FLARE FlTTING A N D H O 8 E
(Figure 8-17)
FITTING
The end of the full
vent
lines should extend 10
degrees
E10
a
CHART.
forward
distance of 1.75 inches below the lower
surface of the wing. The end of the line is scarfed at a 35 de~ee
angle facing forward to ensure a positive vent pressure. Any
from vertical for
TORUUE
FUEL BOOST FUMP REMO VA L
a.
Drain the fuel from the
wing
cells.
8-19
NOTE
of these units results in minute
the formation of
When
a
malfunctioning pump is replaced, the
pump plus the crossfeed valve may be
to drain the affected wing.
destructive effect
opposing
utilized
ozone
leaves
on
sparks
that
gas. Ozone has
fuel
cells.
cause
highly
Although it
a
visible indication, ozone makes the
material of which the cells are formed brittle so
that the cells will disintegrate upon the applicano
tion of stress.
b.
After the fuel is drained,
valve in the OFF
place
the fuel selector
position.
Disconnect all the electrical power to the airplane.
Disconnect the electrical lead to the pump.
Cut the safety wire and loosen the mounting
c.
d.
e.
bracket.
UN/ROYAL FUEL CELL REPAIf~
For information
pertaining to the repair, handling and storUniroyal Fuel Cells, refer to Report FC-1473-73 entitied Recommended Handling and Storage Procedures for
Bladder Type Fuel and Oil Cells", which is published by
U niroyal inc., Engineered Systems De part me nt, M ishawaage of
f.
Remove the
plumbing
to the fuel boost pump.
Note inlet and outlet ports position on pump.
Remove the retaining bolts.
g.
h.
Remove the pump.
ka, Indiana.
FUEL BOOST PUMP INSTALLA TION
NOTE
Position the pump in place, being certain the inlet
are in same position as when pump was
a.
No
repairs are to be made on the radius of a cell
fitting area of the cell. Cells with such
damage are to be returned to Uniroyal Inc., Fuel
Cell Division, Mishawaka, Indiana, for repair.
No damage area larger than 2 inches may be
repaired in the field.
and outlet ports
removed.
b.
Install the retai ning bolts.
c.
Connect the
Safety
d.
plumbing
or
and install the bracket.
wire.
in the
Connect the electrical lead.
GOOD YEAR FUEL CELL REPAIR
CARE AND REPA/R OF FUEL CELLS
The
following is a recommended method of handling bladder-type fuel cell s, includi ng st orage, and post-installation
inspection.
For information pertaining to repair, handling and storage of
Goodyear Fuel cells, refer to Manual AP368 entitled "Repair and Maintenance Manual for Vithane Fuel Cells",
which is
published by Goodyear Aerospace Corporation,
Fabrics Division, Rockmart, Georgia.
Engineering
When
synthetic rubber fuel cells are placed in service, the
gasoline has a tendency to extract the plasticizer from t he
inner liner of the cell. This extraction of plasticizer is not
detrimental as long as gasoline remains in the fuel cell, in as
much as the gasoline itself will act as a suitable plasticizer,
cept
A thin
ratio of 3
a.
Che mical Test.
i.
2.
or
coating
rubbed
on
of
light engine
oil should be flushed, sprayed
the inner liners of all serviceable fuel cells
which have contained
gasoline
will remain without fuel for
installed in
airplanes
or
deformed inside their
plasticizer and
and cracking.
not,
or
than 10
if cells
bays. The
are
oil will act
as a
ex-
Pour ammonia
on
the absorbent cloth in the
maximum.
out
handled until 24 hours
or
fitting openings
per cubic foot of cell
rated cloth inside the cell and install the
Soak
after the oil has been
all
temporary
cc
lein solution, then
The cell should not be removed
to
drying
days, whether
collapsed or
to be
will prevent the inner liner from
plates
capacity. Place the saturemaining test plate.
3. Make up a phenolphthalein solution as follows: add 40 grams phenolphthalein crystals to 1/2 gallon of
ethyl alcohol, mix, then add 1/2 gallon of water.
4. Inflate the cell with air to a pressure of 1/4 psi
if it is evident that the cells
more
Attach test
one.
applied,
smoothly
on
a large white cloth in the phenolphthawring it out thoroughly and spread it
the outer surface of the cell. Press the cloth
down to insure detection of minute leaks.
6. Check the cloth for red spots which will indileak. Mark any leaks found and move the cloth to a
location. Repeat this procedure until the eaird exterior
cate a
CA UTION
Never store fuel cells in the
equipment, such
movement
&20
as
I
new
vicinity
generators and
of brushes
across
of electrical
motors. The
the commutators
surface of the cell has been covered. If red spots appear on
the cloth, they may be removed by resoaking the cloth in the
solution.
7.
The solution and test cloth
are
satisfactory
NOTE
GENERAL INS~RUCTIONS
Repair of the wet wing tip is permissible providing
the damaged area is far enough from the rib to allow
a doubler or plate to be installed. Holes cut to
remove damaged area must be round or at least have
generous radii. Should a stringer be damaged or fall
within the repair area it must be bridged across and
be attached to the repair.
1.
2.
3.
3/8"-~
edges of doubler or plate, rivet butts and nut plates with
Sealer (Items 32 or 33, Consumable Material Chart).
Fill the rivet heads, screw heads and the patch/skin joints with
Sealer (ltems 32 and 33, Consumable Material Chart).
O.IX) psig) before applying filler
Pressure test (0.50 i 0.25
Seal
R IV ETS
/ SCREV\,.0/---i~--.
32"~
7\
DOOR
SKIN
114"
to outer surface.
1/4"
CA UTION
L--
NUTPLATE
It
must be
realized the
is
DOUBLER
wing tip
highly
consequently, the repair structure must be of equal
capability.
wet
stressed
a
area;
REPAIR OF INACCESSIBLE AREAS
1.
Door material
.032 2(324 T3 Aluminum ALCLAD.
Doubler material
.051 2024 T3 Aluminum ALCLAD.
Nut Plates
KIi000-832
Screws
AN507-8R--length to be determined.
AN426AD3--for attaching nut plates.
AN426AD4--for attaching doubler.
Rivets
Rivets
RIVETSFLUSH
2. Two
rows
between
SKIN
gfi f~
_
PATCH
t---1/2"
equivalent.
PLATE
1/4"
---i
or
1/4"
_
_
_
_
3~
3.
4.
rivets in doubler and skin--1!4" E.D., 1/2"
rows
spacing
and rivets.
Single
row of screws through doubler and door--3/8" E.D.,
5/8" spacing. Dimple door and countersink doubler.
Doubler may be cut on one side only in order to place it
inside of cell. Cut side of doubler to be placed on
on
inboard
REPAIR OF ACCESSIBLE AREAS
1.
Rivets
3.
60-608-1
.032 2024 T3 Aluminum ALCLAD
rows
rivets
to be on
through patch
large for entry through access
method for inaccessible area.)
Rivet E.D. f
(patch
plate
openings,
and skin
inner surface of cell. --lf the
is too
use
repair.
.032 2024 T3 Aluminum ALCLAD
Plate material
plate
outboard side of
AN426AD4-5
Patch material
2. Two
or
/4"--spacing 1/2"
between
rows
and
rivets.
4.
Fit flush plate and secure with only
prevent filler from cracking.
enough rivets
to
Figure 8-18. Minor Wet Wing Tip Repair
(TH-669 and after, and Prior Airplanes Equipped
with Wet Wing Tip Kit).
8-21
only
to
long
as
they
as
in immediate
not
use
remain clean. Indicator solution that is
should be stored in a closed container
Connect electrical connections.
c.
d.
prevent evaporation and deterioration,
angles
Move
wing tip
into
position
to the front and rear spars
with
and
secure
support
screws.
Using MS20426AD3 rivets, rivet the connecting
wing and wing tip.
f.
Install the deicer boots (if required) as described in
Section ilunder the heading SURFACE DEICER BOOT
e.
After the test,
remove
all
plates
and test
equipment. Allow
strap
the cell to air out.
both the
to
INSTALLATION.
NOTE
In
conducting
the tests outlined above, the cell
need not be confined
the 1/4
b.
psi
by
a
cage
or
0.00
jig, providing
on
I.
0.25
Pressurize the fuel system using 0.75
0.25
There should be no pressure loss in 15 minutes.
Fuel and restore electrical power to the airplane as
psig.
the
airplane
as
TEST(TH-669 and after)
(Figure 8- 19)
Pressure test fuel cells and vent system to
no drop in pressure.
Ensure that all
a.
completed
b.
the wet
wing tip
are
source
to
the wet
wing tip
as
(TH-669 and after)
external power from the airplane.
and generator switches in the OFF position.
b.
Defuel the airplane, to the point where fuel cannot
be seen from the inboard filler position.
CAUTION
battery
Remove
c.
access
Ensure that the filler cap and access plate s are
This test must be done when the wet
secure.
plates from the outboard lower
wing tip
airplane
wing.
d.
Remove deice boot from
installed)
e.
side of
as
heading
SURc.
Working through the access opening in the under
the wing, loosen the clamps on the 3 inch fuel inter-
connect
f.
and vent lines.
Disconnect the electrical connections,
Support wing tip. Using a 1/8 inch drill bit, drill out
along the connecting strap and re move t he strap.
h.
Remove the support angle screws at the juncture
of the wing tip and wing front and rear spar. Remove the
wing tip.
WET WING TIP INSTALLA TION
Disconnect
3.73
Apply
leak
0.25
psi
external
and generator
(TH-669 and after)
power
switches
from
the
in the OFF
the wet
wing tip
for 5
testing compound MIL-L-25567,
item
to
d.
to
the outside of the
wet
wing tip.
g.
battery
Apply
minutes.
14, Consumable Materials Chart,
rivets
a.
is removed from the fuel system of the
wing tip leading edge (if
described in Section 1 I under the
FACE DEICER BOOT REMOVAL.
Place
to
Figure 8-19.
Disconnect
a.
repairs
and sealed.
Connect pressure
shown in
Place
plates.
LEAK
0.00 for 15 minutes with
WET WING TIP REMOVAL
secure access
required.
follows:
0.75
Install and
h.
i.
pressure is not exceeded.
P,,,,,, t,,t fuel cells installed
g.
airplane.
position.
CAUTION
Mark all leaks
as indicated by bubbles.
Depressurize the wet wing tip, locate and repair
leaks as shown in Figure 8-18.
Repeat the pressurization test procedure and reg.
pair leaks until there is no leakage.
h.
Rinse leak testing compound off the wet wing tip
with clean water and wipe dry with clean cloth.
i.
Install the wet wing tip on the airplane as described in this section under the heading WET WING T1P
e.
f.
INSTALLATION.
LEAKAGE CHECKS AND REPAIRS (WET WING
TIP)
(TH-669 and after)
(Figure 8-20)
Support the wing tip on a platform which will
give firm support but will allow some flexibility
of movement of the wing tip to facilitate proper
alignment. Protect the wing tip surface from
scratches, dents and other damage during installation.
To
classify
measure
ace urate meas ureme nt
b.
Support the wing tip in the proper position to
wing. Connect the hoses from the wing to the 3
interconnect and vent lines. Secure with clamps,
inch fuel
&22
may be obtained by wipi ng t he leakapply talcum powder in the area of the.leak.
minutes, recheck the area to determine if the leak
age clean and
After 30
classifies
attach to the
the degree of leakage in a wet
wing tip fuel cell,
the size of the wet area around the leak. A more
as
a
stain, seep, heavy seep
or
running
leak
as
indicated in Figure 8-20. Fuel leaks must also be classified as
to whether they occur in an
open area or in an enclosed area
to
differentiate between those that require immediate repair
and those not considered
potential flight hazards.
OPEN END
PAES SURE
REOU LATOR7
WATER
MAN6M ETER
WET WING TIP
CLEAN COMPRE55ED
AND/OR FILTERED AIR
PRE 55035 50URCEOF
3.7 3 f 0.2 5 PSIO FOR
5 MINUTES.
PL U G 5
Figure
6-19. Leak Test
Set-up (TH-669
and
after).
RUNNING LEAR
t
3/4" DIA.
O
4"-5"DIA.
STAIN
11/2"DIA.
o
I
SEEP
31/2"-4"Dll\.(
6
MAX.
i
O
AREA WHERE FUEL APP EARS TO PLOW
OR RU N, FOL LOWING CON TOUR OF
SKIN WH EN THIS AR EA 15 WIPED DRY.
FUEL WILL USUALLY BEGIN TO DRI
AFTER REACHING THIS POINT.
HEAVY SEEP
A100-2 31-2 3
Figure
9-20.
Leakage
of Wa
Wing Tip
Fuel
(TH-669 and after).
&23
WARNING
2.
If the
leakage
is around
a
bolt with
a
gasket
type seal, retorque the bolt. If the leak persists, replace the
ANY
leakage
in
an
enclosed
area or
in
quires grounding
until
repair
seal
an area
where the fuel will blow into the fu se lage,
re
is made,
Repair of heavy seeps or smaller leaks in an open
delayed until the airplane is down for ´•other
a.
may be
maintenance.
b.
mediate
ANY leakage in an
grounding and repair.
enclosed
area
requires
im-
Remove any sealant around the leak with a sharp,
c.
nonmetallic tool, such as a tool of chisel-shaped Formica.
Scarf the ends of the
form
a
existing fillet
so
that
or
3.
If the leakage is at the gasket around an acopening or fitting, retorque the attaching hardware. If
leak persists, replace the gasket.
a new
sealant
AIRPLANE DEFUELING
To,,,,,, that all fuel is removed from the system, the fuel
should be drained through the boost pump. To expedite the
defueling operation,
the boost pump may be used to pump
the fuel out of the system. The following steps must be
accomplished before energizing the pump.
can
continuous and smooth tie-in. PR-890B-1/2, Item 31,
Consumable Materials Chart
the bolt.
cess
the
area
or
EC-1675B-1/2, item 32, Con-
a.
Apply external
power to the
airplane electrical
sumable Materials Chart, is recommended for the
system.
b.
process.
and the mixture lever in IDLE CUT-OFF.
sealing
Thoroughly clean the area to be repaired with
methyl ethyl ketone, item 19, Consumable Mate ri als Chart
or naphtha, I te m 1 8, Consu mable Materials Chart, prior to
sealing. The following repairs are permissible:
i.
rivet. This
replace
&24
If the
can
the rivet.
only
leakage is around
be done
once.
a
c.
d.
attach
rivet, restrike the
If the leak
persists,
position
Remove the filler caps to vent the system.
Di sconnect the main fuel line at the firewall and
drain hose. Provide a suitable container for the fuel.
e.
Energize
f.
When the fuel is
plane,
tion.
a
Place the fuel selector valve in the ON
the boost pump.
no
open the sump drains to
longer pumped from the aircomplete the defueling opera-
SECTION
PRESSURIZATION
THIS SECTION IS NOT APPLICABLE TO THE BEECHCRAFT BARONS
91
SECTION
HEATING AND
COOLING SYSTEM
HEATING AND VENTILATION
(TC-I thru TC-1657, TE-1 thru TE-967 (except TE-959)
and TH-1 thru TH436)
Figure 10-1 and Figure 10-2)
the pilot’s and co-pilot’s air vent doors
pedals are controlled by push-pull knobs
located at the extreme left just below the subpanel. The
doors are adjusted at the attachment of the cable and vent
through TH-436,
above the rudder
door
on
the firewall.
THE HEA TER CONTROL SYSTEM
OVERHEAT THERMOSTAT
The heater control system consists of two thermostats. A
thermostat in the heater duct controls the duct temperature
according to its setting, which is varied by the push-pull
in the subpanel. When the
the
all
is
control
way out the heater will
push-pull
automatically shut off when the duct temperature reaches
180 degrees Fahrenheit. The further the control is pushed
in, the lower the temperature at which the heater will shut
control
(CABIN HEAT)
direction
the
sleeve
turned to increase
should be
the
temperature setting. One turn will change the temperature
setting approximately 125 degrees Fahrenheit.
The overheat thermostat is set at the factory to operate at
300 degrees Fahrenheit and ordinarily will not need to be
off.
the heater is set to shut off the
in case the duct
Fahrenheit
degrees
thermostat malfunctions. As in other combustion heater
installations, it is a normally-open thermoswitch which
closes if an overheat condition develops. When closed, it
shorts the heater power supply to ground, blowing a fuse
and shutting down the heater. The fuse cannot be replaced
An overheat thermostat
heater
in
The overheat thermostat is controlled by an adjusting screw
on the bottom of the thermostat. A letter "H" with an
arrow through it on the head of the switch indicates the
at
on
adjusted.
300
flight.
WARNING
Never set the thermostat for temperature above
300 degrees Fahrenheit. The heater is not
designed for higher temperature and fire may
result.
NOTE
or dual heater fuel pump operation is
controlled by the landing gear limit switch.
While on the ground, or with the landing gears
HEA TER SPA RK PL UG GAP
extended, heater operation is supplied by one
heater fuel pump. During flight, or with landing
gears retracted, heater operation is supplied by
inches.
Single
Heater
spark plug
gap should be set from 0.250 to 0.312
HEA TER IGNI~ER POINTS
both heater fuel pumps.
Two sets of heater ignition points are installed in the
vibrator of the heater ignition unit. The primary set of
RIGGING THE HEATER CONTROLS
igniter points has
the far left side of the subpanel
controls the iris valve and the heater safety switch. Place
the iris valve actuator as far to the right (facing forward) as
With the "CABIN AIR" control pushed in, attach
The cabin air control
on
possible.
the control wire to the iris valve actuator arm. The safety
switch is positioned on the underside of the heater shelf in
adjustable slots. Pull the "CABIN AIR" control to the
half-open position
and set the
safety switch
arm so
that the
switch will be open at this point.
operation)
a
service life of 1000 hours,
points should
of points has been
be put in use. When the alternate set
used for 1000 hours, replacement of the vibrator must be
accomplished. Failure to switch to the alternate set of
disturbing the adjustment
of the
safety switch.
The heater ductstat control located at the far right of the
left hand subpanel controls the heater thermostat. With the
pushed in and the lug on the
right, push the control wire thru
Make sure the guide lug on
the
screw.
and
tighten
lug
ductstat switch is in the straight downward position
"CABIN HEAT" control
ductstat pushed to the far
1
the
the
before
securing the control wire. Serials TC-955 thru
TC-1657, TE-1 through TE-967 (except TE-959) and TH-1
to
fail
in service
on
points at 1000 hours may causC the points in
making the alternate set of points inoperative.
The alternate set of points
serials prior to TC-191 by a
can
be
placed
use
point selector switch
the
Serials
on
panel beneath the instrument panel.
through TC-420 the switch is on the left hand
electrical panel. TC-Q21 through TC-1657 the selector
switch is removed and the points are placed in service by
adding a 20 gage jumper wire between terminals "A" and
"B" on the heater ignition unit (see Wiring Diagram,
Section 14.)
circuit breaker
When disconnecting the iris valve control for adjustment
the full-open or
purposes, position the control in either
full´•closed position, so that it may be reinstalled without
theater
at which time the alternate set of
TC-191
through TE-451 the points are placed in service
20 gage jumper wire between terminals "A"
and "B" on the heater ignition unit. Serial TE-452 through
TE-967 (except TE-959) and TH-I through TH-436, the
points are placed in service by a point selector switch on
Serials TE-1
by adding
a
the left hand electrical
panel.
10-1
I’
i
t
X
I
II
3
i
1
~::::;i:::::´•::j:;::::;::::c::.:::c::j.i:::
.i
2
ii
F.
C
B
: : : i: i:j: : ji: : : : j: : : : : : : :;: :~i: i .: s:
D
C
A
HEATER PLENUM DUCT
IGNITOR
Serials TC-1 thru TC-5(11
Airplane
1.
FUSES
2.
HEATER THERMOSTAT
HEATER~ FUEL PUMP
RESISTOR
.-:´•;;.-.´•.-.´•.´•.´•--´•-´•´•´•~,´•;I´•:´•:´•:´•;;:;´•´•;-
ldl
BI~BiB:i.i.i´•Z´•i´•i.i.i l
: .il:1:i :i : : l:I:‘;:I:i #:1: :i ’I: :I:i ;: l:I:l i: : : i:lti:l l.~i
-:::i-:-:´•:-:-:-:´•:-:´•:-´•:´•:-::i:-::::;:::::1:::I:::::::::::::::
ui
j
I,
ilili i iji ji ji’i ’ i ili i i
Y-:-ri7
0
24
n
s:::::::::::::::-j~
"´•-------i~
iuA
:;::::i:::::::-:j::::::::::::~:-:
IGNITOR
lialai is,:-:1:::-::::::I:::
I~r\
25
,I
Airplane
23
22
0
A
Serials TC-502 and After
;f
,1´•:.:.:.:.:.´•;.:.,:.:.:,.: :,: , , ,:,.:.:.:.:.-.;:.´•.I_:.:.:.:o:.,:.:, :.:.,:,.:.:.:,.:.,:.:.:.:.,:.:.:.: : :.:.´•: : : i,: ,;:
1
5
4
6
17
::::::i:::::::;::::::::::::::::::::::::::::::::::::::::
: : :i :i j:lI´•:i :i ;:i :i : ji: : : : : : : : : : : : : : : : : : : :ai: i:Bi: :li : i : i: : : : : : : :r:
i
18
2.
Alternate Points
4.
Iris Valve Control
Rear Seat Outlet
,mi
Defrost
16
I
5.
ii
r::ii:;l:i-:l:I:isi:X:l:i-:iPi i ’:i:i::::::I:
ia li-i-
Switch
-il-´•-.--i´•
i~´•
t’:
:i~
9
I----^.-il.- --i_
Pilot’s Outlet
15
-: i : -: ; : j: ~: : KI:i : :i :)i I: I: I:181:I l: l:i :i l: l:I jf-:i :i :l j:I i:l i l:l: l:i : i: i:j l:I :l :i :i l:i l:"I:l’ :l I:’ i: ´•: i :i I: -: l I: l: I: I: : :I i: :
:I:l:i:l:I:l:i:l:’;:i:]i i :i:itililili’i il i:ilili: i i i:i_: il i i:,:;/
P
14
12
8.
:::::.:.;:.:.:.::li:I::ll lil:III:ll i:il:
C
24
js;: Zil!il .’iIfli’:I’:litl’´•li3il:~i]ji ji i; :i :il li l:i i:l : I:l il il:i li:li -i:-iljil-li i l:il:
27
25
__
19
5
5
18
20
22
A
‘i
´•´•i
´•~C
;1
i
23
r;
E
’~""i
28
FRESH AIR VENT
i
~i::;
D
11.
Solenoid Valve
12.
Heater Overboard Fuel Line
Combustion Fuel Met Line
Effective TC-1 thru TC-954
7
Heater
Spark Plug
17.
Heater
18.
Combustion Air Intake Duct
Iris Valve
Ignitipf
21 115
13
It
3
~rplane Serials
TC-502 thru TC-954
Lead Assy.
22.
Assembly
Safety Switch
Ignition Assembly
23.
Heater Duct Thermostat
24.
DverheatFuse
Heater Resistor
Cabin Heat Switch
21.
25.
26.
17
Heater Shroud Drain
16.
19,
20.
4
i,
Intake Blower
Heater
27.
Cabin Heat Circuit Breaker
28.
Rear Seat Outlet
´•:´•:;´•:´•:´•:´•:;´•-:´•xr
Figure lal. Heat and Vent System TC-1 through TC-954
1~2
(300"F)
10.
15.
3
C
Pump
14~
: : : : j: : .: -.: .: -,:- ,. :- .:- ´•:- ´•:- :- :- :- :- :- :´•:- :- : -: :- ´•:´•:- ´•:- ´•:- ´•:- :- ´•:- :- :- : :
1
Heater Fuel
Overheat Thermostat
Heater Fuel Strainer
Serials TC-I thru TC-501
10
i
L:J ~n
1
i
3 r1
2
iiiiiiiiiiiiiiiiiiijiSi
li’iiiriiiiiiiiiiiiilitiii
ilas:illsi~l
i i i i i iji i i ~i i
B
iiiiiiiiiiiiiiiiiiiiiii
iiijiiiijiiijijiijiiiii
1.
FUSES
:iiiiiiiiilliitiljliiit
2.
iiilililitiiilitiiiiIli
’’’’’I’iX´•’l’b’:
3~
HEATER THERMOSTAT
RESISTOR
C
i iji i i i i i i i i i i
’’’’’I´•’’"’´•’’’’’’’’’’’’
iililiililiiiliiiilii:Iiii
‘iiiililililjifiliiililitii
liiililtiliiiiii.iiiliiiii
HEATER FUEL PUMP
lillliiiliililililiiiiliiiilljl;ii)
S
ilji ilililililji iji lili ililjti i iti.i&ilifi if
iiifililjljilll~
iiiiifiiif
i:l i% iB i i i ij i f jil ij. i ji i ji ij i i ji il i ji i i ji ij ij i
I
i i j:i li i r il i i i li j i i i i i i i li jli ilIjil i :jil i: ~
23
AJ
30
(?4
iji.i.i i li i i lji i i i i i i l:li ili i l’t~
2
I-
IGNITOR
1,
Temperature Control
2,
Defroster Control
Iris Valve Control
Rear Seat Outlet
3,
4,
J
5,
6,
4
Y
7.
i\
8.
I,
3
i
9,
liiijiiiiiiiiij
19
i
i::::~
T~f´• 172i´•ll
Is
i-: _-:I il:-~´•:-I’:I- :-lji_ j l i lji ij il ji li ilj i lj il i jlif ij i i i j i j i j i l i li ir j i i i ji i i
Figure 10-2.
liii 14
8
i:lrli;iiiiliii 12 )ii ilili i ili i li i i jiji i i lili ij~
g
7
Heater Overboard Fuel Line
Combustion FuelMetLine
13´•
HeaterExhaust
14´•
Heater Shroud Drain
Heater Spark Plug
jiiiliiiiiilili
15.
16.
261
(3000F)
Heater Fuel Strainer
Solenoid Valve
12.
iijiiijiiijiiij
iiiijiiiigjl
ii\jjiijiiiiij
_
17,
Heater Ignition Lead Assy.
C,,bUeti, Ai, Intak, Duct
18.
Zrfs valve
iiiililii,llil:
\riliiiii:i~iti-
19,
1
: : : i: i: i: il:’ -:l i: _: i: : I: : : : : : : : : i : i : li: i: I :iI(:i :I :i : : : : ´•: i : i: i: li: li lfi li :i fl i.l
10,
11.
18
Fresh Air Scoop
Pilot’s Outlet
Heater Fuel Pump
Overheat Thermostat
Intake Blower Assembly
20, Heater Safety Switch
21, Ignition Assembly
22, Heater Duct Thermostat
23, OverheatFuse
24, Heater Resistor
25, Heater and/or Blower Switch
26. TXlct to Rear Seat Outlet
27, Pilot’s Air Control
28, Co-Pflot’s Air Control
29, Canopy Fresh Air Vent
i: l: i:I i: il: I:l I: l :.1l:i :ifI1 :i l:i :i :i :i l:i :i l:i l:i l:I1 :i li li :i :iI :i :i] :Ii : i : i : i : i : i : i : i : iI: i : i : iI: li:
: i-´•: i’: ’I:i ’ i ’l ir li .li ri :i rl i il i l :i l i ijr i l’.i lri: i :ir ji i.li tcli ti .tl4Si i li ij i li j li i
Heat and Vent System !TC -955 thru
TC-1657, ’75-’1 thru ’75-958
and TE-960 tt;ru TE-967, TH-1 thru
TH-436)
10-3
HEATEROVERHAUL
5.
the
The heater should be overhauled and pressure tested
every
500 hours of heater operation in accordance with the
Midland-Ross Maintenance and Overhaul Manual, P/N
30C57.
t´•IEA TER SOLENO/D VAL VE
Check the valve operation by connecting a 24-volt de
power
source with an ammeter with a 0-1 ampere
range in the line.
Turn the power on and off several times. The valve should
draw 0.26 amperes current and click when the valve opens.
To check for valve leakage, apply 35 psi air pressure to the
inlet end of the valve and submerge the outlet end in water
(check
more
direction of flow arrow on valve). If the valve leaks
than 20 bubbles per minute, clean the valve and
recheck.
core
When
with
reassembling
the spray nozzle,
tighten
screwdriver and the strainer with the
a
fingers.
Cleaning
the
SparkPlug.
cleaning, examine the spark plug for
evidence of cracked or broken porcelain, arcing or carbon
tracks inside the well of the spark plug. If cracks are found,
discard the plug. Arcing or carbon tracks may be caused
by
shorting of the plug or by dirt on the spring connector that
seats in the well of the spark plug. In either case the fault
should be corrected before reinstalling the plug.
2. Wipe out the inside of the well of the spark
plug with a clean cloth dampened with carbon
c.
i.
Before
tetrachloride.
3. Close the
sandblast the plug.
COMBUST/ON
INSPECTION
plug
well
CHAMBER
with
AND
a
stopper and
RADIATOR
To clean the
valve, wipe all parts with a soft cloth saturated
solvent, making sure that no solvent gets in the
electrical parts. Inspect the plunger cap, seal and spring.
Replace these parts if worn or damaged. Blow out the valve
body with compressed air before reassembling.
with
a.
Slight scaling and discoloration of the combustion
chamber and radiator assembly is a normal condition on
heaters that have been in use. The scale will be mottled and
a blue powder can be rubbed off of the scaled
areas. This
does not constitute ground for rejecting the heater since
considerable life can still be expected if there are no soft
spots in the metal where it has been subjected
CLEANING THE HEA TER
Cleaning the Combustion Chamber and
Assembly can be accomplished using either of
following methods:
a.
Radiator
the two
Soak the combustion chamber and radiator
an Oakite M-3 stripper solution for 10 hours.
assembly
The solution is made by mixing one pound of Oakite
(Oakite Products, Inc., 22 Thames Street, New York 6,
New York) with each gallon of water used. The solution
should be maintained at a temperature between 190 to 210
i.
in
degrees Fahrenheit during the soaking period. Flush the
heater thoroughly with water after it is removed from the
Oakite solution.
2. Use a stainless steel brush or sandblast to
b. Severe overheating will result in general
weakening
of the metal that results in soft and
spongy spots. These are
usually found directly opposite the crossover passages.
They can be detected by tapping lightly with a ball peen
hammer. This will give a slightly soft or spongy
response in
contrast to a solid feel when tapping on live metal. These
soft spots will usually have a dull
gray appearance
indicating
considerable surface oxidation. The presence of
soft spots is reason for rejecting the combustion chamber
and radiator assembly.
I CA UTION
remove
any accumulation of carbon or other foreign
material from the inside of the combustion chamber. Clean
thoroughly with compressed air.
b.
1. Disassemble the spray nozzle by unscrewing
the fuel strainer and two piece core from the nozzle body.
2. Clean the parts in Stoddard solvent.
3. If soaking fails to thoroughly clean the parts,
4.
body,
The
a
soft, non-metallic brush.
gro6ves in the core and orifice in the
may be cleaned with
a
soft
pointed piece of wood.
NOTE
Do not
it will
nozzle.
10-4
If any soft spots are located in the combustion
chamber and radiator assembly, there is a
malfunction in the heater system and a new
heater should be installed until trouble has been
corrected.
Cleaningthe SprayNozzle.
scrub them with
use a
alter
to severe
overheating.
REMOVING
HEA TER
INSTALLING
THE
CABIN
Remove the
nose cone attaching screws, disconnect
light wiring on airplanes incorporating the optional
taxi light and remove the nose cone.
a.
the taxi
b. Disconnect the iris valve control and blower
wiring.
Remove the clamp that secures the blower to the
support
bracket.
metal tool for
cleaning the parts as
the flow characteristics of the
AND
c.
Remove the ftve bolts that attach the iris valve to
and lift the blower and iris valve from
the
fiberglass plenum
the
plenum.
d.
plug
Disconnect the heater ignition lead from the
and heater
spark
the electrical
ignitor.
Disconnect the combustion air flexible tubing from
the combustion air inlet at the heater,
Remove the fiberglass plenum from the heater by
f.
removing the clamp and asbestos strip.
g. Disconnect the fuel inlet line from the solenoid in
the nose wheel well and the drain line at the heater fuel
e.
perpendicular approximately 84.
m. Make certain the clamps securing the inlet and
outlet plenums are properly positioned to prevent damage
to the plenums.
Use Presstite No. 576, (product of Presstite
n.
Engineering Company, St. Louis, Missouri) as required
when reinstalling the iris valve,
REMOVING AND INSTALLING
HEA TER BLOWER
THE
CABIN
attaching screws, disconnect
airplanes incorporating the optional
nose cone
light wiring on
taxi light and remove the
the taxi
b.
nose cone.
Disconnect the electrical
wiring
at the blower.
Disconnect the iris valve control at the iris valve.
d. Removetheblower attachingclamp.
Remove the five bolts that attach the iris valve to
e.
the fiberglass plenum and remove the blower and iris valve.
Installation is the reverse of removal procedure.
f.
c.
seal between
When installing the blower, check for a good
the iris valve and fiberglass plenum. Apply additional No.
576 Presstite Sealer (product of Presstite Engineering
Company, St. Louis, Missouri)
as
necessary,
REMOVING AND INSTALLING
HEATER IGNITION UNIT
To
remove
the heater
ignition unit,
THE
CABIN
disconnect the wiring at
ignition
unit
remove
the
by reversing the
REMOVING AND INSTALLING
HEA TER SPA RK PLUG
a.
b.
the
unit.
removal
c.
THE
CABIN
Remove thenose cone.
Remove the heater blower and iris valve.
Disconnect the spark plug lead and remove the
spark plug.
Installation is the
d.
Use
a
standard
reverse
of the removal
procedure.
thread lubricant.
spark plug
REMOVING AND INSTALLING THE
HEA TER FUEL DISCHA RGE NOZZL E
a.
b.
Remove the nose cone.
Disconnect the combustion air nexible
CABIN
tubing from
the combustion air inlet at the heater.
Disconnect the heater ignition lead at the ignition
c.
unit and remove the clamp securing lead to iris valve
assembly.
d. Remove the blower attaching clamp and
disconnect the iris valve control. (See Figure 10-1).
Unfasten the clamp securing fiberglass plenum to
e.
the heater and lift plenum and blower assembly forward.
f.
Remove the
the
Reinstall
Disconnect the heater shroud drain line in the nose
wheel well.
Remove the clamp securing the plenum to the rear
i.
of the heater.
j. Remove the two clamps securing the heater in the
wheel well.
k. Remove the eight heater attaching bolts that secure
the heater supporting ring to the No. 1 bulkhead and
remove the heater from the nose section.
Installation is the reverse of the removal procedure.
i.
When installing the heater position the support ring and
gasket so that the heater exhaust extends to the left of
plug, disconnect the ignition lead,
attaching screws and remove
procedure.
inlet.
h.
a.
unit
ignition
remove
Disconnect the ignition lead at
plenum and blower assembly.
spark plug
and
the
Remove the fuel inlet cover, if installed, and
g.
disconnect the combustion fuel inlet line.
h. Remove the two screws securing the fuel inlet
shroud assembly and remove the shroud assembly and the
i.
fuel inlet elbow.
Disconnect the aerating line at the heater forward
j.
Remove the fuel
90-degree
end.
heater and
remove
the
discharge nozzle body from the
discharge nozzle using a 5/8-inch
socket wrench.
k. Flush the heater fuel system before reinstalling the
fuel discharge nozzle.
Reinstallation procedure is the reverse of the
i.
removal procedure. When securing the inlet plenum to the
heater, make certain that the clamp cleats are positioned
between the plenum and the heater or the cleats may
damage the plenum.
10-5
TROUBLESHOOTING HEATER SYSTEM
TC-1 through
TC-1657, TE-1 through TE-967 (except TE-959) and TH-1 through TH-436
INDICA nON
Blower runs but
i.
heater will not start,
PROBABLE CAUSE
a.
Blown fuse.
REMA RKS
a. Check ductstat operation; check
combustion chamber and ducts for
obstructions.
b.
Faulty ignition
unit vibrator.
b. Switch to reserve vibrator contacts.
If this corrects trouble, replace vibrator
first opportunity.
at
c.
Faulty ignition
unit coil,
Remove lead from spark plug and hold
spark may jump to structure. If
no spark, repair or replace ignition unit.
c.
so
d.
Faulty spark plug.
e.
Fuel solenoid valve not
energized,
d. If test in (c) produces spark,
and clean or replace spark plug.
e.
remove
Check electrical connections. Discon-
nect fuel line and check for fuel flow.
Replace defective valve.
f. Fuelfilter
g.
clogged.
Spray nozzle clogged.
h. Insufficient combustion air.
i.
Faulty differentialpressure
switch.
2.
Heater will not shut off
a.
Defective ductstat.
automatically.
f. Clean filter.
g. Clean spray nozzle.
h. Remove obstructions or repair leaks.
Check for combustion blower operation.
i. With heater ON, check terminals to ascertain if
switch is open.
a.
Connect
should
3.
Heater backfires
intermittently,
continuity meter
across
a.
Loose connection in control B
or loose ignition lead to
a.
close, completing
the circuit.
Check electrical connections.
circuit
spark plug.
b. Mixture too rich.
c.
Restriction in combustion
air duct.
b. Make checks in item 4 below.
Check duct for obstruction,
and combustion blower for
c.
proper operation.
4.
Fuel mixture too rich;
exhaust
smudges fuselage.
a.
Restriction in combustion
air duct.
a. Check ducts for obstructions
and combustion blower for proper
operation.
b. Restriction in exhaust duct.
c.
Loose
core
in fuel nozzle.
b. Check exhaust outlet.
c.
Clean nozzle. Make sure
tightly in shell.
is seated
d. Both pumps
gear extended.
108
duct-
stat leads and operate control. As the
control is pulled out, ductstat switch
operating with
d. Check limit switch.
core
TROUBLESHOOTING HEATER SYSTEM (Cont’d)
INDICA TION
5.
Heater
inadequate
produces
heat.
PROBABLE CA USE
a.
Thermostat not
REMA RKS
properly
a.
Adjust
thermostat.
adjusted.
b. Fuel filter partially
c.
clogged.
Restriction in fuel lines.
b. Clean filter.
c.
Clean line
or
otherwise
remove
restriction.
d. Iris valve
opening
d. Check limit switch to
too
small.
e.
operate
Restriction in air ducts.
e.
at
1/2 opening.
Check air valve and ducts for
obstruction.
f.
Spray
nozzle
g. One pump
retracted.
partially clogged.
operating with
gear
f. Clean spray nozzle.
g. Close L. G. limit switch and check
both pumps for operation.
10-7
HEATING
AND VENTILATION
TE-968 and after and TH437
(TC-1658 and after, TE-959,
and after)
(Figure 10-3)
THE HEA TER CONTROL SYSTEM
the
lug and tighten the screw. Make sure the guide lug on
the ductstat switch is in the straight downward position
before securing the control wire. The pilot’s and co-pilot’s
air vent doors above the rudder pedals are controlled by
push-pull knobs located at the extreme left just below the
subpanel. The doors are adjusted at the attachment of the
cable and vent door on the firewall.
The heater control system consists of two thermostats. A
thermostat in the heater duct controls the duct temperature
according to its setting, which is varied by the pusl;-pull
control (CABIN NEAT) in the subpanel. When the
push-pull control is all the way out the heater will
automatically shut off when the duct temperature reaches
180 degrees Fahrenheit. The further the control is pushed
in, the lower the temperature
OVERHEAT THERMOSTAT
The overheat thermostat is set at’the factory to
operate
between 260 and 325 degrees Fahrenheit and can not be
adjusted, but must be replaced if it malfunctions.
at which the heater will shut
off.
HEA TER SPA RK PL UG GAP
An overheat thermostat on the heater is set to shut off the
heater between 260 and 325 degrees Fahrenheit in case the
duct thermostat malfunctions. On TC-1658 through
The
proper gap.
TC-1722, TE-959, TE-968 through TE-990 and TH-437
through TH-496, it is a normally closed thermoswitch
HEA TER IGNITION UNIT
which opens in an overheat condition breaking the circuit.
When the heater has cooled sufficiently, the switch will
reset completing the circuit again,
On TC-1723 and
after, TE-991 and after and TH-497 and
after, the thermoswitch is a normally closed circuit breaker
which opens in an overheat condition breaking the circuit.
The circuit breaker must be manually reset before the
heater will operate again. The circuit breaker can not be
reset while the airplane is in night.
spark gap is .156 to .188 inch. The gap may be
adjusted by moving the ground electrode to obtain the
The electric current for the ignition is supplied by the
ignition unit, which converts 24 volt direct current to high
voltage oscillating current. This provides a continuous spark
across the gap of the spark plug during heater
operation.
Inspect and repair in accordance with Maintenance
Instructions for Ignition Unit Assembly Manual, P/N
93D00-1, Janitrol Aero Division, Midland-Ross
Corporation.
HEA TER O VERHA UL
NOTE
There is
only
heater fuel pump in this
system which furnishes fuel to the heater on
the ground or in the air.
one
At the end of each 500 heater operating hours, or after
each heating season (whichever comes first), remove the
heater from the airplane for pressure test of the combustion
tube, complete inspection of heater parts and any necessary
overhaul operations. Inspect and overhaul in accordance
with Maintenance Instructions for Aircraft Heater Unit
Assembly, P/N 92D88-1, Janitrol Aero Division,
Midland-Ross Corporation.
RIGGING THE HEATER CONTROLS
The cabin air control on the far left side of the subpanel
controls the iris valve and the heater safety switch. Place
the iris valve actuator as far to the right (facing forward) as
COMBUSTION TUBE PRESSURE TEST
possible.
With the "CABIN AIR" control pushed in, attach
the control wire to the iris valve actuator arm. The safety
At each
switch is
leaks
positioned on the underside of the heater shelf in
adjustable slots. Pull the "CABIN AIR" control to the
half-open position and set the safety switch arm so that the
switch will be open at this point.
When
disconnecting
the iris valve control for
adjustment
position the control in either the full-open or
full-closed position, so that it may be reinstalled without
purposes,
disturbing the adjustment
of the
safety
switch.
The heater ductstat control located at the far right of the
left hand subpanel controls the heater thermostat. With the
"CABIN HEAT" control pushed in and the lug on the
ductstat pushed to the far right, push the control wire thru
10-8
as
overhaul,
pressure test the combustion tube for
follows:
Make sure that all openings except the combustion
a.
air pressure switch connection are plugged. This is the most
convenient connection for attaching the test air pressure
source.
b. Connect a regulated air pressure supply to the
opening that has not been plugged. Apply a pressure of
three to six psi to the combustion tube.
c.
Submerge the assembly in water for several
minutes while
watching for bubbles that would indicate
leaks. Turn the combustion tube in the water so that
any
entrapped bubbles will be freed. Bubbles will indicate leaks.
Small
leaks, if accessible, can be repaii~ed.
15
9
1
i
k!
i,ii
~tSi
~b
i
16
24
s
Is
DETAIL A
!ill)
s
23
25
i
2?
1~
a
2
1
2~
~8‘
I
19
7
Ij
13
DETAIL B
fa
17
A
14
12
1´•
1.
Temperature Control
2.
Deiroster Control
3.
Iris ValveControi
4.
Rear Seat Outlet
5.
Fresh Air
6.
Pilot’s Outlet
7.
Hearer Fuel Pump
8.
OverheatThermostat
9.
Fuelvalve
Scoop
(3000FI
10.
Heater Overboard Fuel Line
11.
Combustion Fuel inlet Line
12.
Heater Exhaust
13.
HeaterShroud Drain
14.
Heater Spark
15.
Plug
Heaterlgnition LeadAssy.
16.
CombustionAir IntakeDuct
17.
iris Valve
18.
Ignition Assembly
19.
Heater Dunihermostat
20.
Heater and/or Blower Switch
21.
Ductro RearSeatOvtiet
22.
Piler’s Air Control
23.
Co-Pilo~’s Air Control
24.
Canopy FreshAirVent
25.
Cabin HearCircuitBreaker
55-411-4
Figure 10-3.
TE-968
Heat and Vent System (TC-1658 and after. TE-959.
and after, TH-437 and after)
’19-9
CLEANING ~HE HEA TER
Cleaning
a.
Assembiy
following
the Combustion Chamber and Radiator
be
can
chamber and radiator assembly is a normal condition on
heaters that have been in use. The scale will be mottled and
a blue powder can be rubbed off of the scaled
areas. This
accomplished using either of
the two
does not constitute ground for rejecting the heater since
considerable life can still be expected if there are no soft
methods:
spots in the metal where it has been
i.
Soak the combustion chamber and radiator
assembly in an Oakite M-3 stripper solution for 10 hours.
The siilution is made by mixing one
pound of Oakite
(Oakite Products, Inc., 22 Thames Street, New York 6,
gallon of watts used. The solution
New York) with each
should be maintained
temperature between 190 to 210
degrees Fahrenheit during the soaking period. Fiush the
heater thoroughly with water after it is removed from the
Oakite solution.
2.
Use
at a
stainless steel brush or sandblast to
remove any accumulation of carbon or other
foreign
material from the inside of the combustion chamber. Clean
thoroughly
a
subjected
to severe
overheating.
b.
Severe
overheating will result in general
of the metal that results in soft and
spongy
These are usually found directly opposite the
weakening
i
spots.
They can be detected by tapping Lightly
ball peen hammer. This will give a slightly soft or
spongy response in contrast to a solid feel when tapping on
live metal. These soft spots will usually have a dull
crossover passages.
with
a
gray
indicating
considerable surface oxidation. The
presence of soft spots is reason for rejecting the
combustion chamber and radiator assembly.
appearance
with compressed air.
CAUTION
b.
Cleaning
the
Spray Nozzle.
If any soft spots are located in the combustion
chamber and radiator assembly, there is a
malfunction in the heater system and a new
Disassemble the spray noule by unscrewing
i.
the fuel strainer and two
piece core from the nozzle body.
Clean the parts in Stoddard solvent.
3. If soaking fails to thoroughly clean the
parts,
scrub them with a soft-non-metallic brush,
3.
j~ The grooves in the core and orifice in the
may be cleaned with a soft pointed piece of wood.
body,
heater should
not
be installed until trouble has
been corrected.
REMOVING
CABIN HEATER
NOTE
NOTE
The heater
Do not
it
will
use a
metal tool for
alter
the
flow
cleaning
the parts as
characteristics of tfie
Remove the
a.
the
core
with
When
a
reassembling
the spray nozzle, tighten
screwdriver and the strainer with ~he
fingers.
be removed without
can
be
removing
accomplished more
readily if the shelf is loose
nozzle.
5.
can
the radio shelf, but
nose
nose
cone
removed.
or
attaching
screws
and the
cone.
b.
Disconnect the iris valve control, blower wiring
and the
igniter
leads.
Remove the bolts attaching the iris valve to the
heater and forward support.
d.
Remove the screws and remove the forward
support.
e.
Remove the screws holding the exhaust pipe and
c.
c.
Cleaning
i.
the
Before
Spark Plug.
cleaning,
examine the spark plug for
porcelain, arcing or carbon
tracks inside the well of the spark plug. If cracks are found,
discard the plug. Arcing or carbon tracks
may be caused by
shorting of the plug or by dirt on the spring connector that
seats in the well of the spark plug. in either case the fault
should be corrected before reinstalling the plug.
2. Wipe out the inside of the well of the
spark
plug with a clean cloth dampened with carbon tetrachloride.
3. Close the plug well with a
stopper and
sandblast the plug.
evidence of cracked
or
broken
remove
the
f.
heater.
Disconnect the fuel lines from the heater and
cap
g´•
the
openings.
h.
i.
plates
i.
while
10-10
Slight scaling
and discoloration of the combustion
remove
the
two
heater drain
Disconnect and
remove
the hot air duct from the
heater.
Remove the aft
k.
a.
Disconnect and
lines.
j´•
COMBUSTION CHAMBER AND RADIATOR
INSP~CTION
pipe.
Remove the combustion air flex duct from the
to
on
clamp from
around the heater.
from the upper and lower
the No. 1 bulkhead and remove the plates.
Grasp the healer on the forward end and pull
Remove the
screws
rotating the heater
surrounding
clear the
to
the
right
structures.
and left,
as
required,
NOTE
The cabin heater
blower, heater ignition unit
and the heater fuel
integral part of
discharge
the heater and
nozzle
are
are
an
removed with
the heater.
f.
Connect the fuel lines
g.
Replace
the
to
the heater.
combustion air flex duct
to
the
heater.
h.
Connect
the exhaust
pipe
with
the
attaching
screws.
i.
Replace the forward support and
attaching screws.
Connect the iris valve to the heater
j.
attach with
and forward
support with bolts and connect the iris valve control,
blower wiring, and igniter leads.
INSTALLING THE CABIN HEATER
k.
Replace
the
nose cone
with the
attaching
screws.
NOTE
The cabin heater
blower, heater ignition unit
and the heater fuel
discharge
nozzle
are
REMOVING THE CABIN HEA TER SPARK PLUG
an
integral part of the heater and must be installed
with the beater.
a.
Remove the
b.
On the left side of the heater, disconnect the
spark plug lead and
a.
Grasp the heater on the back end and push while
rotating the heater right and left, as required, to clear the
surrounding structure.
b.
Replace the upper and lower plates on the No. 1
bulkhead with the attaching screws,
c.
Replace the aft clamp around the heater.
d.
Replace and reconnect the hot air duct on the
heater.
e.
El
Connect the
two
heater drain lines,
nose cone.
remove
the
spark plug.
INSTALLING THE CABIN HEATER SPARK PLUG
Lubricate th~e heater spark plug with
a.
spark plug lubricant.
b.
a
standard
On the left side of the heater install the heater
spark plug, and spark plug lead.
c.
Replace the nose cone.
10-11
aeec~craft
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING HEATER SYSTEM
TC~1658 AND AFTER; TE-959, TE-968
AND AFTER; TH-347 AND AFTER
INDICATION
PROBABLE CAUSE
i. Blower runs but heater will
not start.
REMARKS
a. Overtemp circuit breaker
tripped,
a. Check ductstat operation;
check combustion chamber and
ducts for obstructions.
b.
Faulty ignition
unit vibrator,
b. Replace vibrator
opportunity.
c.
Faulty ignition
unit coil.
c. Remove lead from spark plug
and hold so spark may jump to
structure. If no spark, repair or
replace ignition
d.
Faulty spark plug.
d. If test in
remove
at first
unit.
(c) produces spark,
or replace
and clean
spark plug.
e.
Fuel solenoid valve not
energized.
e.
Check electrical connections.
Disconnect fuel line and check
for fuel flow. Replace defective
valve.
f. Fuel filter in fuel pump
f. Clean filter.
clogged.
g.
Spray
noule
clogged.
h. Insufficient combustion air,
g. Clean spray noule.
h. Remove obstructions
repair leaks. Check for
combustion blower
i. Faulty differential pressure
switch.
2. Heater will not shut off
a.
Faulty ductstat.
automatically,
i. With heater
or
operation.
ON, check
terminals to ascertain if switch
is open.
a.
Connect continuity meter
ductstat leads and
across
operate control. As the control
is pulled out, the ductstat switch
should close, completing the
circuit.
3. Heater backfires
Loose connection in control
circuit or loose ignition lead to
a.
intermittently,
a.
Check electrical connections.
spark plug.
b. Mixture too rich.
c. Restriction in combustion air
duct.
b. Make checks in Item 4.
Check duct for obstruction.
Check combustion blower for
c.
proper operation.
4. Fuel mixture too
exhaust
rich;
smudges fuselage,
Restriction in combustion air
duct,
Check iris valve. Check
ducts for obstruction.
b.Restriction in exhaust duct.
b. Check exhaust outlet.
a.
c.
Loose
core
in fuel noule.
a.
c.
Clean nozzle. Make
core
10-12
is seated
tightly
sure
in shell.
E15
~eechcraft
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING HEATER SVSTEM
TC-1658 AND AFTER; TE-959, TE-968
AND AFTER; TH-347 AND AFTER (Contil7ued)
INDICATION
5. Heater
produces inadequate
heat.
PROBABLE CAUSE
a.
Thermostat not
properly
REMARKS
a.
Adjust thermostat.
adjusted.
b. Fuel filter in fuel pump
b. Clean filter.
partially clogged.
c.
Restriction in fuel lines.
c.
Clean line or otherwise
restriction.
remove
d. Iris valve
opening
too small.
d. Check limit switch to operate
at
e.
i.
Restriction in air ducts.
Spray
noule
partially
112 opening.
Check air valve and ducts for
obstruction
e.
f. Clean spray noule.
clogged.
AIR-CONDITIONING SYSTEM
(TE- 1 119,
TE- 1125 AND AFTER; TH-873, TH-895
AND ATTER)
NOTE
On serials TE-1119, TE-1125 and after
through TH-1744 the refrigerant used on the original installation is
R-12. On serials TH-1745 and after the
refrigerant used is R-134a.
and TH-873
conditioning system
falls outside the normal
operating
range. Both pressure sensing switches are wired to
common 5-ampere fuse located on the left nacelle.
The
high pressure switch
and relief valve
are
a
incorpo-
rated into the system to protect against a high pressure condition. The high pressure relief valve is
located in the left nacelle in the pressure discharge
line immediately before it enters the condenser. It is
set to bleed off excess pressure in the event pressure
exceeds 450 psi.
The
optional air-conditioning system is a recirculating
air-cooling-refrigerant
system controlled by two
switches located on the left subpanel. The on/off air-
The
conditioner switch engages the compressor clutch circult and the hi/to evaporator blower switch controls the
output of the forward and the aft evaporator blowers.
is shorted
The system is wired through the landing gear downlimit switch and the left landing gear safety switch. If
the air-conditioning is in operation and the airplane is
ground, power through the left landing gear
switch
causes the condenser air scoop to fully
safety
At
the
same time, power through the landing
open.
downlimit
switch causes the condenser blower to
gear
With
the
airplane airborne and the landing
operate.
the
power through the left landing gear
gear retracted,
on
the
safety switch causes the air scoop to partially close to
a flight position. The landing gear downlimit switch is
opened, removing any power from the condenser
blower for inflight conditions,
pressure-sensing switches and a high pressure
relief valve protect the air-conditioning system from
operating any time the pressure within the airTwo
515
high pressure
switch is located in the left nacelle
in the pressure line and is set to activate at 375
5
psi. When the switch is activated, the 5-ampere fuse
through a resistor to ground and power is
removed from the compressor magnetic clutch. The
high pressure switch will automatically reset when the
pressure drops to 250 25 psi but further operation of
the compressor cannot be obtained until the cause of
the
the
high pressure has been isolated and repaired
5-ampere fuse has been replaced.
and
The low pressure switch is also located in the left
nacelle and is installed in the suction line. This switch
is
designed to actuate when the pressure drops to 7
psi. When this switch is actuated, the 5-ampere fuse
common to both high and low pressure switches is
again shorted through a resistor to ground and power
is removed from the compressor magnetic clutch. Further operation of the compressor cannot be obtained
until the air-conditioning has been serviced or repaired
and the 5-ampere fuse is replaced.
1
10-13
BARON 55 AND 58
SHOP MANUAL
FWD EVAPORATOR
SERVICE VALVE
MODEL
58
HIGH
PRESSURE
SWITCH
m
RELIEF
VALVE
CONDENSER
I\ ~I
I
MODEL
E55
FS
1IIII
1
Jllil
FS
\39.001
\49.00
ISIGHT GLASS
SERVICE VALVE
DRYER
111 11
/1X
,SERVICE VALVE
FRONT SPAR
L__
LOW
PRESSURE
SWITCH
H11
1
I
1111
1
FS
100.00
REAR SPAR
FS
131 .00
IIII
NOTE
I
__
THE SERVICE VALVES ON THE
COMPRESSOR AND IN THE AREA
OF BOTH EVAPORATORS WERE
REMOVED AT TH-1745 AND AFTER.
FRONT
SPAR
IIII
1
I
FS
151 .00
FS
170.00
FS
190.
SERVICE VALVE
FS
100.00
REAR SPAR
AFT
EVAPORATOR
TE-1140 AND AFTER
C95TH2181660 6
Figure
10-14
10-4.
Alr-Conditloning Plumbing
815
aeec~ncraft
BARON 55 AND 58
SHOP MANUAL
PRECAUTIONARY SERVICE MEASURES
refrigerant oil on-all tube joints and dip the O-ring in
assembling the joint to help ensure a
leak-proof joint. Use oil (35, Consumable Materials
Chart, Section 2) for this purpose on airplanes TH-1
thru TH-1744. RL 100S oil (67, Consumable Materials
Chart, Section 2) is used on airplanes TH-1745 and
this oil before
WARNING
I
Due to the air qriallty control regulatlons enacted In the United States,
R-12 and R-f34a refrigerant cannot be
vented into the atmosphere. When
performing maintenance on the airconditioning system where R-f2 or
R-134a can escape from the system,
evacuate the
or
system with
recycle servicing
refrigerant.
after.
I ´•-´•I´•´•I
WARNING
A face shield should be
recovery
unit that will sal-
vage the
tasks that will maintain this system in
tioning order.
reasons
NOTE
for these measures
in the compressor. Moisture
into ice at
formation
The
are
for
safety
entering the sysleaky valves or
may not only freeze
expansion valves, but can also cause the
of hydrochloric or hydrofluoric acids in the
receiver-dryer
is the last
assembly
to be connected. This is necessary to
ensure maximum moisture protection of
proper func-
a
and to prevent dirt and moisture from
tem. Dirt contaminants may cause
wear
con-
sight.
the work should be thoroughly familiar with instructions on servicing the system. These instructions
should be followed very carefully when performing the
major
when
lines
tact with the eyes can cause loss of
Before any service is attempted which requires opening of refrigeration plumbing or units, the person doing
The
worn
performing maintenance on the
because refrigerant coming In
a
the
refrigeration system.
a´•
This is
ing
a
b.
Whenever
high pressure system. When disconnectrefrigerant line, the system must be discharged
a
a
refrigerant
purge the entire system with
ing at the 125-micron level.
line is disconnected,
a vacuum
pump operat-
system.
All subassemblies
are
drated.
They
making
connections.
are
shipped
They
I
sealed and
to remain sealed until
dehyjust prior to
should be at
room
tem-
Insufficient torque when tightening tubing connections, can result in loose
joints and excessive torque can result in
deformed joint parts. Either condition
can result in refrigerant leakage. Refer
to step c for correct torque values.
perature before uncapping. (This prevents condensation of moisture from the air that enters the
system.)
If for any reason caps are removed, but the connections are not made, then the tubes and other parts
should not remain unsealed for more than 15 minutes,
If the time period is longer, reseal the connections.
c.
All
a"t
precautions should be taken to prevent damage to
fittings or components. Even minute damage to a connection could cause it to leak. Any fitting getting
grease or dirt on them should be wiped clean with a
cloth dampened with alcohol. Do not use chlorinated
solvents such as trichlorethylene for a cleaning agent,
for they are a contaminant. If dirt, grease or moisture
gets inside pipes and
have to be
515
cannot be
replaced. Use
a
removed, the pipe will
small amount of clean
CAUTION
When
connecting
aluminum
fittings
in the
refriger-
System, torque all 5/8-inch fittings to 18-21 footPOU"dS and all 1/2-inch fittings to 11-13 foot-pounds.
d.
Use refrigerant R-12 (item 34, Consumable Materials Chart, Section 2) in this system on airplanes
TH-1 thru TH-1744 or R-134a (Item 68, Consumable
Materials Chart)
Other refrigerants,
chloride, will
components.
airplanes TH-1745 and after.
particularly those containing methyl
cause rapid deterioration of aluminum
on
10-15
I
Qeechcraft
BARON 55 AND 58
SHOP MANUAL
leak
exceeding
Do not smoke when servicing the
system because the refrigerant converts to a
exposed
to
more
toxic gas when
open flame.
ounce a
ounce a
A useful device may be made of a 1/4inch copper tube for detecting shaft seal
leaks on an installed compressor.
SYSTEM LEAK DETECTION
Acquire
a 12-inch-long tube and put a
90" bend 314 inch from the end. Insert
the straight’end into the detector hose
NOTE
and insert the other end into one of the
holes in the compressor clutch plate.
It is
permissible to add 4 ounces of
refrigerant leak detector dye (70, Consumable Materials Chart, Section 2), to
the suction side of the refrigerant system
CLUTCH TEST
to detect leaks. A red film will appear in
the areas of leakage.
A reduction of system cooling ability, or the
presence
of bubbles in the refrigerant, may indicate a partial
loss of refrigerant. The sight glass should be checked
Check the clutch amperage. The clutch should draw
approximately 1.7 amps. A poor ground could be the
cause of low voltage or amperage. If the voltage or
amperage is incorrect, check that there is a good
groumd. If clutch engagement is erratic, use a feeler
SaSe to check the air gap. A gap of 0.016 to 0.030
inch is required for proper_engagement,
during operation at maximum available ambient and
temperature. Streams of bubbles past the glass
or foam in the glass indicates an inadequate
refrigerant quantity. If a loss of refrigerant is suspected; an
inspection of the system plumbing should be carried
out to locate the source of the leak. Large leaks
may
be located by the appearance of oily spots where oil
has been carried out by escaping refrigerant. Smaller
If a faulty pulley (clutch) bearing is suspected, remove
the belt and check for roughness. Disengage the
clutch and turn the pulley by hand. If there is rough-
leaks, which
UNUSUAL NOISE
cabin
detected
are
much
difficult to locate, may be
or an electronic detecthe above detectors, the system
more
by detergent bubbles,
tor. In order to use
must contain a
partial charge and be operating. The
detergent test is accomplished by covering a suspected area with soap suds and watching for bubbles.
An electronic detector has a probe which is moved
along the plumbing to pick up escaping refrigerant.
Refrigerant is heavier than air so the probe should be
held below the lines. Various types of electronic and
fluorescent leak detectors are available and each type
a somewhat different manner. The detector manufacturer’s instructions should be reviewed for
proper usage of the instrument. If a leak is detected at
operates in
fitting, the use of a soft copper flare gasket in
fitting is permissable if the connection does
seal by the normal method.
I
0.3
NOTE
highly
an
than 0.5
year, any other leak
year should be repaired. Any
area suspected of leaking should be cleaned with
soap and water.
WARNING
ness,
replace the
bly
bearing
or
rotor
pulley
and clutch front
assem-
set.
If tere is unusual noise in the compressor, check the
following:
a´•
Loose belt; torque to 80 to 90
b.
Broken bracket and/or compressor
c.
Missing,
d´•
LOW
broken
or
foot-pounds.
mounting.
loose bolt at the compressor.
’efrigerant level;
restore the proper
refriger-
a"t level.
AIR-CONDITIONING FUNCTIONAL TEST
With the
engine running at 1000 rpm and the system
sight glass, if the refrigerant appears
bubbles appear, charge the system as noted
on, observe the
a
the
flare
milky
not
in CHARGING THE AIR CONDITIONING SYSTEM in
Section 2. Check the system for leaks using a flameless leak detector.
Any
or
leak detected with soap bubbles or Halide flame
detector is leaking sufficiently to require repair. Electronic detectors are very sensitive and may detect
leaks that are small enough to be insignificent. While
a.
compressor shaft seals should be
the compressor belt.
10-16
repaired only
if
they
COMPRESSOR BELT REMOVAL
Remove the left
engine cowling
to
gain
access
to
E15
aeechcraft
BARON 55 AND 58
SHOP MANUAL
b.
Remove the
propeller per Section
2.
Loosen the adjustment bolt on the idler pully
bracket to remove tension on the compressor belt.
c.
d.
Remove the compressor belt.
b.
Install the compressor belt over the compressor
drive pulley.
Tighten
the
adjustment
bolt
on
the idler
pulley
the compressor belt per
COMPRESSOR BELT TENSION ADJUSTMENT in
this section.
I
c.
Install the
d.
Install the left
sure
the belt has
ample clearance
on
CONDENSER BLOWER REMOVAL
pully, idler pully and
bracket to increase tension
tension, make
all sides.
COMPRESSOR BELT INSTALLA TION
a.
a belt tension gage, placed at the midpoint between
the idler pulley and the compressor, will register a belt
tension of 75 to 90 pounds. After adjusting the belt
on
propeller per Section
2.
engine cowling.
a.
Gain
access to
the condenser blower in the left
nacelle.
b.
Tag and disconnect the electrical
blower motor.
Remove the
blower.
attaching
c.
wiring
hardware and
to the
remove
the
CONDENSER BLOWER INSTALLATION
COMPRESSOR BELT TENSION
ADJUSTMENT
After 36 to 48 hours
operating, a new belt will stretch
to its normal operating length. The belt tension should
be checked at this time and adjusted by torquing the
adjustment bolt, located on the pulley bracket, so that
a.
Place the condenser blower in position.
b.
Secure the blower by
installing
the
attaching hard-
ware.
c.
Connect the electrical wiring to the blower motor.
d.
Install
access
panels and
secure.
ONDENSER
DOOR
NACELLE
STA.
67.0
NACELLE
STA.
83.0
OUNTING ASSY. 8
BLOWER
93.88
ACTUATOR
LCONDENSER
COIL
UFF PAD
\LDUCT ASSY.
55/58-426-10
Figure
515
10-5. Condenser and Blower
10-17
I
aeechcraft
BARON 55 AND 58
SHOP MANUAL
CONDENSER REMOVAL
a.
Open
b.
Remove the
remove
the left
b. Remove electrical leads from compressor clutch
terminals.
engine cowling.
screws
from the
engine
air scoop and
I
the scoop.
Remove the screws from the two skins
of the left nacelle and remove the skins.
c.
on
the
top
d.
Remove the
e.
Disconnect the air scoop door actuator and
the actuator.
screws
Disconnect the instrument air line over the aft end
of the condenser and remove the air line.
f.
conditioning system
where R-12 or
escape from the system,
evacuate the system with a recovery
or recycle servicing unit that will salvage the refrigerant.
R-134a
g. Remove the screws from the three brackets over
the aft end of the condenser and remove the brackets.
Using
the system
recycle/recovery service unit, discharge
slowly, through the service ports under the
a
copilot’s seat,
Disconnect the freon lines to the condenser.
j.
Cap
k.
and
The
until all pressure is bled off.
i.
plug
all
con-
Remove the bolts from the forward end of the
a.
Place the condenser in
b.
Secure the condenser
position.
by installing
the bolts.
Remove the caps and plugs and install the inlet
c.
and outlet lines and secure.
d.
Charge
e.
Install the instrument air line.
the system
as
indicated in Section 2.
f.
Install the three brackets.
g.
Place the two skins in
and install the
place
and install the
i.
Install the actuator to the air scoop door.
j.
Place the
the
screws.
k.
Closetheengine cowling.
air scoop in
position
and install
Gain
10-18
access
highly
toxic gas when
to an open flame.
c.
Using the service valves in the fuselage forward of
the main spar, slowly discharge the system with the
recovery recycle servicing unit until all pressure is bled
off.
d.
Disconnect refrigerant lines at the compressor.
Cap the refrigerant lines and compressor fittings.
f’
Remove the four compressor mounting bolts and
REPLAC/NG COMPRESSOR
a.
Drain oil from the
b.
Drain and
new
measure
compressor.
the oil from the old compres-
sor.
c.
COMPRESSOR REMOVAL
a.
exposed
nuts and remove the compressor.
screws.
engine
high
Remove the compressor belt per COMPRESSOR
BELT REMOVAL in this section.
position
Place the air scoop door in
a
e.
screws.
h.
converts to a
Lift the condenser up and out of the nacelle.
CONDENSER INSTALLATION
Is
Do not smoke when servicing the
system with R-~2 or 1344 because It
con-
denser.
m.
air-condltlonlng system
125-micron level.-
denser.
i.
can
pressure system. Before dlsconnecting a refrigerant line, the system must
be discharged with a recovery seflllcing unit. Purge the entire system to a
openings.
Remove the bolts from the aft end of the
I
Due to the air quality control regulatlons enacted In the United States,
R-12 and R-134a refrigerant cannot be
vented into the atmosphere. When
performing maintenance on the alr-
from the air scoop door.
remove
h.
´•U´•,.,
WARNING
to the LH
engine
accessory section.
Measure
new
oil
(35
or
67, Consumable Materials
Chart, Section 2) equal
to the amount drained from
the old compressor and
use
it to refill the
new com-
presser.
515
~eechcraft
BARON 55 AND 58
SHOP MANUAL
NOTE
I
If the oil level in the old compressor cannot be determined, then the oil should
be drained from the entire system and
the system reserviced in accordance
with REPLENISHING AIR CONDITIONING SYSTEM LUBRICATION in Section
2. Drainage can be accomplished by
after
performing maintenance on
conditioning system where
the freon line fittings at low
the system. Approximately one
of oil will remain in the system
R-134a
can
the alrR-f2 or
escape from the system,
system with a recovery
evacuate the
draining,
or
recycle servicing
refrigerant
unit that will sal-
vage the
If any contamination of the system is
the system should be flushed
The
suspected,
as
I
Due to the air quality control regulations enacted in the United States,
R-f2 and R-~34a refrigerant cannot be
vented Into the atmosphere. When
cracking
points in
ounce
wU´•,,,
WARNING
alr-condltlonlng system
Is
a
high
pressure system. Before dlsconnectIng a refrigerant line, the system must
noted in FLUSHING THE SYSTEM in
this Section.
be
discharged with a recovery servlcIng unit. Purge the entire system to a
COMPRESSOR INSTALLATION
125-micron level.
NOTE
Do not smoke when
Check and service the compressor with
oil as noted in REPLACING COMPRESSOR in this section.
system with R-12
It converts ~to
exposed t~
Position compressor on the mounting bracket and
attaching bolts and nuts.
a.
install the
b.
Install the compressor belt as noted in COMPRESSOR BELT INSTALLATION in this Section.
e.
Adjust
belt tension
as
noted in COMPRESSOR
I
f.
Purge
the system
as
Using the service valves in the fuselage fonnrard of
slowly discharge the system with the
recovery/recycle servicing unit until all pressure is
bled off.
b.
Disconnect both hose connections to the
When
flushing with AC Flush, do not
allow it to enter the compressor.
clutch.
noted in FLUSHING THE
c´•
Remove and discard the filter-drier.
hose connection and allow
Of the AC Flush to enter
Section 2.
condenser.
Install and
secure
the
access
panels.
FLUSHING THE SYSTEM
It is necessary that the air-conditioning system be
flushed and evacuated when the system has been
contaminated. The system can be flushed by using
AC Flush (69, Consumable Materials Chart, Section
liquid cleaning agent and dry nitrogen as a
propellant. Flushing of the system may be
accomplished as follows:
2)
as a
515
the discharge
approximately one pound
the discharge side of the
Connect the
dry nitrogen container at the same
with pressure set between 100 and 250 psig.
Allow pressurized vapor to enter until all flushing liquid
e.
point
is
vapor
com-
NOTE
g. Charge the system with refrigerant as noted in
CHARGING THE AIR-CONDITIONING SYSTEM in
h.
when
a.
Remove caps from lines and compressor and
install lines to the fittings on the compressor.
magnetic
highly toxic gas
open flame.
the main spar,
d.
Install the electrical leads to the
servicing the
R-134a because
presser.
BELT TENSION ADJUSTMENT in this section.
e.
a
an
or
purged
out of the inlet to the filter-drier hose
con-
nection.
t
9.
Cap
both connections.
Remove the
expansion valves and clean.
h.
Using the above procedure, flush and purge the
liquid hose from the filter-drier to the expansion valves
and suction hose and
evaporator.
10-19
I
~)eechcraft
BARON 55 AND 58
SHOP MANUAL
i.
Evacuate the system as noted in R/ACUATING
THE SYSTEM in this Section.
The alr-condltlonlng system Is a high
pressure system. Before disconnecting a refrigerant line the system must
be discharged with a recovery servlc-
EVACUATING THE SYSTEM
Using
a
system
recycle/recovery
as
ing
service unit, evacuate the
follows:
Attach the LO service hose of the
recovery unit to the suction port.
a.
b.
Attach the HI service hose to the
c.
Adjust the
vacuum
unit.
Purge
the entire system to
A face should be
worn when performIng maintenance on the lines because
refrigerant coming In contact with the
eyes can cause loss of sight.
recyclel
discharge port.
to control the turbulence of the
Do not smoke when
servicing the
R-134a because
highly toxic gas when
oil in the pump.
system with R-12
d.
It converts to
As the pump-down progresses and the turbulence
reduces, gradually open the vacuum and HI and LO
valves until
tion
they
efficiency,
fully open
are
for maximum
evacua-
When the pressure is down to about 200 microns,
close the valve to
the
f.
The system must be evacuated to 125 microns
lower.
or
FORWARD EVAPORATOR BLOWER
MODULE REMOVAL
Gain
module
b.
the forward
evaporator blower
baggage compartment.
The module is located to the
forward
e.
the forward
access to
through
rear
left side of the
baggage compartment,
Using
a
or
to an open flame.
recycle/recovery service unit, discharge
slowly, through the service ports under the
a
copilot’s seat,
until all pressure is bled off.
Remove the air-conditioning hoses and ducts
g.
from the evaporator blower module.
h.
Remove the evaporator blower attaching bolts
and remove the evaporator blower module.
FORWARD EVAPORATOR BLOWER
MODULE INSTALLATION
a.
Place the forward evaporator blower module in
position
and
secure
with
attaching
bolts.
Remove tags from the electrical wiring and
evaporator blower module.
con-
nect the wires to the
Remove the screws from the metal guard around
the evaporator module and remove the guard from the
airplane.
Tag and
f.
b.
Removethe blanketfrom thefloor.
d.
e.
exposed
the system
I .e.nwopermit
d-p
mup
continuing
a.
a
125mlcron level.
c.
Connect the
air-conditioning system
hoses and
duct to the evaporator blower module.
Place the metal guard in position around the
evaporator module and install the screws.
d.
remove
the electrical
wiring
from the
evaporator blower module.
e.
Charge the refrigerant system
as
indicated in Sec-
tion 2.
I
~ING
w´•w,,,
f.
g.
Due to the air quality control regulations enacted in the United States,
R-fP and R-l34a refrigerant cannot be
Install the blanket
Close the
on
the floor.
baggage compartment
door.
FORWARD EVAPORATOR BLOWER
MOTOR REMOVAL
vented Into the
atmosphere. When
maintenance
on the alrperforming
R-12 or
where
conditioning system
R-134a can escape from the system,
evacuate the system with a recovery
or recycle servicing unit that will salvage the
10-20
refrigerant.
a.
Gain
motor
b.
through
to the forward
the forward
evaporator blower
baggage compartment.
The module is located to the
forward
c.
access
rear
left side of the
baggage compartment.
Remove the blanket from the floor.
515
~echcraft
BARON 55 AND 58
SHOP MANUAL
B.L. 0.00
OW
DUCT
UCT
CO
NVT
WASHER
\Ih
LII
I
I
f--EVAPORATOR
MODULE
WASHER
NUT a
WASHER
FIL
F.S. 39.00
GROMMET----L,1,
RACKET
DUCT
APORATOR
MODULE
I
SEAL
NUT
TUBE
WASHER
WASHER
UCI
p
F.S. 190.00
Tu
DRAIN P
ASSY.
FLANG
ASSY.
DRAI
55/58-427-4
Figure
515
10-6.
Evaporator
Modules
10-21
BARON 55 AND 58
SHOP MANUAL
d. Remove the screws from the metal guard around
the evaporator module and remove the guard from the
be
airplane.
123-micron level.
e.
Tag
and
remove
evaporator blower
f.
g.
Remove the
the electrical
wiring
discharged with a recovery servlcIng unit. Purge the entire system to a
A face shield should be
from the
screws
from the fan closure,
Remove the motor and fan from the evaporator,
Place the motor and fan in
position
on
servicing the
with
R-12
R-134a
because
or
system
Et converts to a highly toxic gas when
exposed
the evapo-
to
an
open flame.
d.
b.
the fan and motor
holding
inplace.
c.
Remove the
tag and install the electrical wires
on
the motor.
d.
air-conditioning hoses
and ducts
Remove the evaporator blower attaching bolts
e.
a"d remove the evaporator blower module.
guard
in
position
around the
INSTALLA TION
screws.
a.
f.
Remove the
AFT EVAPORATOR BLOWER MODULE
Place the metal
evaporator module and install the
e.
con-
Do not smoke when
f’om the evaporator blower module.
screws
lines
sight.
rater.
Install the
when
tact with the eyes can cause loss of
FORWARD EVAPORATOR BLOWER
MOTOR INSTALLATION
a.
worn
performing maintenance on the
because refrigerant coming in
motor.
Install the blanket
Close the
on
the floor,
baggage compartment
Place the aft evaporator blower module in
attaching bolts.
position
and secure with
door.
b.
Remove tags from the electrical wiring and
evaporator blower module.
con-
nect the wires to the
AFT EVAPORATOR BLOWER MODULE
REMOVAL
I
a.
Open
the aft
baggage compartment
doors.
Connect the air-conditioning system hoses and
duct to the evaporator blower module.
c.
d.
Charge the refrigerant system
as
indicated in Sec-
tion 2.
b.
Remove the lower
(held
c.
in
portion
of the aft bulkhead
e.
by velcro).
Tag
and
remove
evaporator blower
the electrical
wiring
from the
f.
g.
motor.
Check the
refrigerant
Install the lower
Close the aft
line connections for leaks.
portion
baggage
of the aft bulkhead.
door.
AFT EVAPORATOR BLOWER MOTOR
I w´•w´•´•I
REMOVAL
ARNING
Due to air quality control regulations
enacted In the United States, R-12
and R-134a refrigerant cannot be
vented into the atmosphere. When
performing maintenance on the air-
conditioning system
R-134a
where R-12
or
escape from the system,
system with a recovery
servicing unit that will sal-
can
evacuate the
or
recycle
refrigerant
alr-condltlonlng system
Is
a
high
pressure system. Before disconnect
ing a refrigerant line,
10-22
Open the
b.
Remove the lower
(held
c.
in
Tag
aft
baggace compartment
portion
doors.
of the aft bulkhead
by velcro).
and remove the electrical
evaporator blower
wiring
from the
motor.
d.
Remove the
e.
Move the motor and fan aft and away from the aft
screws
from around the fan closure.
blower module.
AFT EVAPORATOR BLOWER MOTOR
vage the
The
a.
the system must
INSTALLATION
Place the motor and fan in
blower module.
a.
position
on
the aft
E15
Qeechct~ft
BARON 55 AND 58
SHOP MANUAL
b.
Install the
in the fan closure.
f.
Remove the tags and install the electrical
c.
on
screws
Checkthatthefan operates.
e.
Install the lower half of the aft bulkhead.
Close the aft
baggage compartment
doors,
EVAPORATOR BLOWER MODULE
FILTERS
Clean filters with
air-conditioner
ever
compressed air every 100 hours of
operation and replace the filter when-
the filter material is discolored
air-conditioner
operation
whichever
or
at 500 hours of
occurs
first,
AFT EVAPORATOR BLOWER MODULE
FILTER CLEANING
Locate the air outlet at the top of the bulkhead at
FS 190.00. Remove the air-outlet louvered molding
a.
Remove
FRESH AIR VENT BLOWER SYSTEM
An
optional fresh air blower located in the aft fuselage
provides additional ventilation through the overhead
outlets during ground operations. The blower utilizes
the
upholstery panels
from the bulkhead at
FS 190.00.
c.
Using clean compressed air, back blow all dust,
sand and other contaminates out of the filter.
Install the
upholstery panels
with the filter
attached.
Install the air outlet louvered
e.
ducts and air outlets
gain
access
to the blower
b.
Remove the
c.
Tag
d.
Remove
rear
clamps from
Remove the blower
Position the blower
on
the
mounting
Install the
appropriate clamps
Connect the electrical
wiring
to the ducts and
to the blower assem-
bly according
tags or
wiring diagram manual.
f.
Install the
the BEECHCRAFT Baron
upholstery panel.
I"stall the fifth and sixth seats if necessary.
ADJUSTING THE U(PANSION VALVES
Remove the filter from the back of the
upholstery
panel.
Using No. 77 spray adhesive (Item 38, Consumable Materials Chart, Section 2), bond a new filter to
the back of the upholstery panel,
d.
515
assembly
c.
e.
panel.
bolts from the
Install air ducts to the blower inlet and outlet.
plate.
Allow adhesive to
attaching
b.
electrical
e.
the blower ducts and dis-
support bracket and install the attaching bolts.
a.
c.
wiring.
and support bracket.
to the
from the bulkhead
to
the
FRESH AIR V~NT BLOWER
INSTALLA TION
d.
upholstery panels
on
upholstery panel.
and disconnect the electrical
mounting plate
tighten.
Remove the
(if installed)
mounted
connect the ducts from the inlet and outlet.
FILTER REPLACEMENT
b.
assembly
aft bulkhead.
AFT EVAPORATOR BLOWER MODULE
at FS 190.00.
the standard fresh
Remove the fifth and sixth seats
a.
molding plate.
Locate the air outlet at the top of the bulkhead at
FS 190.00. Remove the air outlet louvered molding
as
FRESH AIR VENT BLOWER REMOVAL
a.
d.
same
air system.
e.
plate.
b.
molding plate.
(OPTIONAL)
d.
f.
wiring
the motor.
Install the air outlet louvered
dry
and install the
upholstery
Even though the expansion valves are of the adjustable type, it is impossible to properly adjust them on
the airplane. The expansion valves are adjusted at the
factory to 38 ~t .05 psi. Without proper equipment a
satisfactory adjustment can not be achieved. If the
valves are not operating properly replace the valves
with
new ones.
10-23
aeechcraft
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING
AIR-CONDITIONING SYSTEM
TE-1119, TE-1125 AND AFTER; TH-873, TH1895 AND AFTER
TROUBLE
1. Insufficient
cooling,
PROBABLE CAUSE
a.
Blower not
functioning.
b. Obstructed
duct.
2. No
cooling.
Compressor
Evaporator
filter
e.
Refrigerant
level low,
a.
Blown fuse, loose connection.
unit.
Hissing
or
belt
slipping.
clogged.
functioning,
b. Remove obstruction
c.
Repair
d.
Replace.
e.
Leak-test and
adjust.
or
b.
Repair.
recharge.
c.
Leak-test and
d.
Compressor valves inoperative.
d.
Repair
e.
Slipping
e.
Tighten
or
a.
Overcharged.
a.
Correct
refrigerant charge.
b. Air in system.
b.
Purge
c.
Tighten.
Mount
or
or
broken belt.
compressor bolts loose.
pulley
a.
Compressor
b.
Faulty belt,
c.
Low
or
and
loose.
d.
Tighten.
oil level low.
a.
Add oil.
replace.
recharge system.
Replace.
c.
Add
hitting shroud,
d.
Align
e.
Faulty compressor.
e.
Replace.
in evaporator
a.
Low
a.
Add
knock in
a.
Faulty expansion valve.
a.
Replace.
a.
Loose.
a.
Adjust.
b.
Overcharged.
b. Correct
c.
Air in system.
c.
Evacuate and
a.
Pulleys
not in line,
a.
Align pulleys.
tight.
b.
Adjust
refrigerant
level.
charge.
recharge.
replace.
b.
or
repair.
a. Check connections, fuse,
continuity, and proper -22ustment of
expansion valves.
module.
6. Chatter
or
Leak in system.
d. Fan
5.
clutch
Repair.
c.
d. Drive
Noisy
disconnected air
c.
c.
4.
a.
d.
b. Blower not
3. Excessive vibration of unit.
or
REMARKS
refrigerant.
and
tighten shroud.
refrigerant.
evaporator module.
7. Belt
slipping.
8. Excessive belt
wear.
b. Belt too
9. Broken belt.
refrigerant level.
recharge.
c.
Belt width wrong,
c.
replace.
Replace with correct
a.
Pulleys
a.
Align pulleys. Replace
b.
Replace
with correct belt.
c.
Replace
and
not in line.
b. Belt width wrong,
c.
Belt
was
too
tight.
or
adjust
belt.
belt.
to correct
tension.
10-24
E15
SECTION
UTILITY SYSTENIS
WARNING
OXYGEN SYSTEM
The oxcygen system consists of an oxygen regulator, oxygen
outlets, and an oxygen cylinder. The oxygen cylinder may be
located either behind the aft cabin bulkhead or in the nose
baggage compartment.
The system may be fitted with either a
or 65 cubic foot oxygen cylinder.
38 cubic foot, 38 cubic foot
On
early
model Barons, oxygen cylinder pressure is
a pressure gage and controlled by a shut-off
monitored with
Keep fires, cigarettes and sparks away when
are in use. Open and close all oxygen
valves slowly. Inspect the filler connection for
cleanliness before attaching it to the filler valve.
Keep tools, hands and components clean, as fire
or explosion may occur when pure oxygen under
pressure comes in contact with organic material
outlets
such
as grease or
oil.
valve located either forward of the cabin aft bulkhead orjust
forward and left of the pilot’s seat. On Barons, serials
TC-955 and after, TE-I and after, and TH-I thru TH-556,
cylinder pressure is connected directly to the pressure gage
on the console. The pressure gage indicates the supply (psi)
of oxygen available. System operation may be limited to
altitudes above 5,000 feet by an optional nltitudecompensating regulator whose sensine element meets each
increase in altitude with increased oxygen flow. On serials
TC- 1673 and after, TE-976 and after, and TH-1S7 and after,
the oxygen cylinder is mounted forward of the cabin forward
bulkhead. The cylinder (of either 19 or 66 cubic foot
capacity) includes an nltitude-compensaring regulator and
cable-operated shutoff valve. The handle for the shutoff
valve is located on the left subpanel in front of the pilot. The
oxygen supply pressure gage is mounted near the pilot’s
outlet on the left sidepanei. The other outlets are located in
the sidepanzls near the seats for which they provide service.
The filler valve is located forward of the cylinder to the right
of the airplane centerline. An overboard vent is installed on
the right side of the airplane. The oxygen masks for the pilot
and copilot an stowed in a box attached to the spar cover
under their respective seats. The third and fourth seats masks
are stowed in boxes attached to either the front or rear of the
oft spar cover, depending on the seating arrangement. The
masks for the fifth and sixth seats are stowed in boxes
attached to the bottom of the seats. While the system forward
CAUTION
All persons handling and servicing oxygen
systems should review proper precautions to be
observed during servicing. FAA Advisory
Circular 43,13-1A contains the necessary
information.
OXYGEN LOW PRESSURE TEST PROCEDURE
(TC-502 and after, TE-1 and after, TH-1 and a~rer)
WARNING
and sparks away from the
of the oxygen cylinder. Hands, clothing
and tools should be clean. Oil and grease will
Keep fire, cigarettes
vicinity
ignite
upon
contact
with pure oxygen untler
pressure.
a.
Turn the oxygen to the full off
position (use
the
push-pull knob).
b.
Disconnect the oxygen low pressure line from the
and cap the open line.
Plug an oxygen gage (0 to 100 psi range) into any
of the cabin forward bulkhead remained essentially the same,
the cabin was redesigned at serials TC-2340, TC-2355 and
regulator
after; TE-1152, TE-11S1 and after; and TH-1027,
TH-1067, TH-1067, TH-1OYO and after. All of the
outlet.
the center
passenger outlets were moved to the headliner near
of the airplane, while the pilot’s and copilot’s outlets
remained in their sidepanels. At serials TH- 1389, TH- 1396
and after, the pilot may stow his mask in a place he considers
Pressurize the system to 60-80 psi with
d.
MIL-0-27210 oxygen, then allow the system to stabilize for
2 minutes.
The pressure drop should not exceed 5.0 psi during
e.
convenient while the copilot’s mask must be stowed in a box
attached to the spar cover under his seat. The third and fourth
seat masks are both stowed in a single box attached to either
the next 15 minutes.
spar cover, depending on the
for the fifth and sixth seats
masks
seating
is not in
are stowed in 3.box under the seats. When the system
loss. For
use, shut off the control valve to prevent oxygen
system servicing refer to Section 2.
the front
or
back of the
rear
nrranrement. The
E10
c.
f.
if the pressure test is
satisfactorp,
reconnect
the
line disconnecred in step ’´•b."
Pressure test the connection made in step "f" by
g.
using cylinder pressure (1500 psi or higher in the cylinder!,
and leak
test
compound, (11.
Section 2).
After the test,
h.
wipe
Consumable
the
area
~Ioterials
clean and
Chart,
drq´•.
11-1
BEECHCRAFT
BARON 55 AND 58
SHOP MANUAL
OXYGEN HIGH PRESSURE 7~EST PROCEDURE
(TC5Q2 and after, TE-I and after, TH-I and after)
diaphra~m
when
wiping
the interior of the face
Si]
cushion.
WARNING
Wipe
c.
and tools should be clean. Oil and grease will
ignite upon contact with pure oxygen under
pressure,
Check
a.
1500
psi
or
to
system
is charged
or
sure
(check
WARNING
Observe the pressure gage; there should be no
pressure drop in 2 hours.
If the leak test is not satisfactory, use leak test
d.
not use oxygen intended for medical
purposes, or such industrial uses as welding.
Such oxygen may contain excessive moisture
that could freeze up the valves and lines of the
Do
Consumable Materials Chart) on the system
connections until the leak is located.
Make the necessary repairs and repeat step iic."
e.
compound(lJ,
the tested
areas
clean and
filling the ox)´•gen system,
only MIL-0-27210 Avintor s Breathing
oxygen system. When
dry.
use
Oxygen (17,
a.
Prepare
a
Constant Flow
cleaning
Mask)
solution
by mixing
one ounce
of
antiseptic 16iF. Consumable Il/laterials Chart, Section 2) (or
equivalent) into two gallons of warm (no hotter than 140" F.)
distilled
The oxygen system may be rid of obnoxious and offensive
odors by purging. The system should also be purged any time
the system pressure falls below 50 psi or the lines have been
purging operation consists
recharging cart filler hose
to the oxygen filler valve and allowing oxygen to flow
through the system and escape at the outlets carrying away
the bad odors. The following steps outline the procedure for
purging the oxygen system.
left open for
water.
of
NOTE
Wear Protective
gloves.
nothing
a.
b.
Do not allow any of the cleaning solution to enter
the reservoir bag or the tlow indicator,
Using a soft cotton clol:h
or
gauze
pad dipped in the
cleaning solution, wipe the exterior of the mask facepiece,
reservoir bag, flow indicator and the oxygen tubing.
CAUTION
Use caution
11-2
not
to
a
period of time.
more
The
than connecting
Connect
a
line from
a
a
recharging cart to
the oxygen
filler valve.
CAUTIC)N
b.
Consumable Materials Chart,
Section 2).
OXYGEN MASK CLEANING
(Puritan-Bennett
cotton
the
c.
Wipe
soft
OXYGEN SYSTEM PURGING
the shut-of’f valve is off
push-pull knob).
f.
a
gauze
to
higher.
Make
b.
make certain the
the interior face cushion with
pad dipped in the cleaning solution.
d.
Using distilled water and a soft cotton cloth or
pauze pad, wipe the areas just cleaned to remove any residue
of the cleaning solution.
e.
Dry the mask.
f.
Place the mask in a clean plastic bar.
cloth
Keep fire, cigarettes and sparks away from the
vicinity of the oxygen cylinder. Hands, clothing
damage the dilution valve
c.
Slowly open
Slowly open
the oxygen supply.
the high pressure line valve
on
the
oxygen control console, to left of the pilot.
d.
Plug in an oxygen mask at each outlet in the cabin
and
cockpit.
e.
Open
f.
all doors and windows.
Set the cart pressure
regulator
to
deliver 50
psi
to
the system.
.411ow system to purge for one hour and check for
g.
the presence of odor. If the odor is still present continue
purging for one additional hour. If the odor is still present
after the second hour of
purging replace
the
supply cylinder.
E1B
BEECHCRAFT
BARON 55 AND 58
SHOP MANUAL
OXYGEN CYLINDER REMOVAL
This
(TC-l’ihru TC-501)
cylinder
has
a
service life of ~380
WARNING
cylinder must
retest
Keep fire, cigarettes and sparks away from the
vicinity of the oxygen cylinder. Hands, clothing
and tools should be clean. Oil and
grease
will
ignite
upon contact with pure oxygen under
pressure.
The oxygen bottle on the above noted airplanes is located
behind the aft cabin bulkhead and ma)´• be removed as
follows:
be tested every five years and
date. Service life on this cylinder is
TE-1 thru
24
Start
a.
only
engine
one
2200 rpm.
b.
Position the
Slowly
engine
c.
Cap
mercury. If the gage does
immediately
with
a
valve.
clean metal
not
the
limited.
TE-j5f)
(TC-1 thru TC-190)
(Figure 11-1)
Disconnect the line from the supply cylinder.
supply cylinder
stamped with
ADJUSTING THE VACUUM SYSTEM
b.
the open line
or
VACUUM SYSTEM
CTC-1 thru TC-2002,
a.
close the oxylgen
pressurizations
years, whichever occurs first, and then must be discarded.
The regular weight cylinder is stamped 3A or jAX. This
vacuum
and check the
and
set
the throttle
selector valve
gage
not
to
reading
the
to
obtain
operating
for 5 inches of
indicate 5 inches:
fitting.
d.
Loosen the bracket
e.
Raise the c~´•linder
clamp wing nuts.
clamps and remove the cylinder
i.
central
from the brackets.
2.
the
thru
a.
TC501)
Place the
new
counterclockwise
cylinder
in the brackets and close the
cylinder clanlps.
b.
Tighten the bracket
Carefully inspect
clamp wing nuts.
fittinys on both the cylinder
the
and the line for cleanliness and the presence of foreign
matter, which may contaminate the oxygen.
decrease suction.
c.
Stop the engine and repeat steps’’a’’ and"b" with
opposite engine running.
d.
After both vacuum regulators have been
individually adjusted to obtain 5 inches of mercury, remove
Connect the line
fitting
to
the
the tape from the central relief valves.
cylinder fitting.
Slowly
open the supply cylinder valve.
f.
Test the connections for leaks with Oxygen System
Leak-Test Compound (Item 14, Consumable Mnterinls
If
Chart.)
obtained
e.
to
the
c.
d.
vacuum
of 5 inches of mercury. Loosen the lock nut and turn the
adjusting screw clockwise to increase suction or
OXYGEN CYLINDER INSTALLATION
(TC-1
Tape the air intake screen on the bottom of the
regulator.
With the engine running at 2200 RPMI adjust
regulator in the naceile to obtain a fage rendiIlp
vacuum
NOTE
a
not
OXYGEN CYLINDER REMOVALAND INSTALLATION
(TC-502 and after, TE-1 anc’ after and 7H-I and after)
reading
agree, check for restrictions in the vacuum
to the engine
system lines from the selector gage
not
agreeing.
The removal and installation of the oxygen cylinder for the
above noted airplanes is the same as airplanes prior to serial
RPM. Then
TC-502, except the cylinder is located in the
of the instrument
nose
baggage
of 5 inches of mercury has been
engine and the other engine does
on one
e.
Start both engines and set throttles to obtain 2200
adjust the central vacuum regulntorjust forward
panel
to
obtain n,OaEe
reading of 5
compartment.
mercury.
OXYGEN CYLINDER RETESTING
ADJUSTING THE VACUUM SYSTEM
(TC-191 thru TC-2002; TE-I thru TE-451)
Oxygen cylinders
used in the Baron
are
of
two
types. The
(Figure 11-1, 11-2,
and
inches of
I
11-3)
liPht-weight cylinder is
stamped jHT on a plate on the side of
th~e cylinder. This cylinder must be hydrostatically tested
every three years and the test date stamped on the cylinder.
EtO
a.
Start
only
one
engine
and set the throttle to ob~nin
2200 RPkI.
11-3
BEECHCFIAFT
BARON 55 AND 58
SHOP MANUAL
b.
Adjust the appropriate vacuum regulator behind
panel to obtain a gage reading of l.S to -t.9
inches,f mercury. Shut down engine.
c.‘ Repeat steps "a" and "b" with the opposite
the instrument
running,
engine
both
regulators have been
engines and set throttles to
individually adjusted,
obtain 2200 RP~VI. The gage reading should then be between
After
d.
vacuum
start
both
5.0 and 5.~ inches of mercury.
airplane. The frequency of cleaning or replacing the air filters
will depend upon sen´•ice conditions: however, they should
be checked approximately every LOO hours of operation.
When operating in localities where there is an excessive
amount of sand or dust in the air, or when subjected to
continuous cabin smoke (tobacco, etc.) the filter should be
inspected, and if necessary, replaced at more frequent
intervals. Under extremely dusty conditions, it may be
necessary to inspect the filter daily. A clogfed tilter reduces
air flow and slows up the rotor, causing a loss of gyroscopic
inertia and
improper
_nyro indication.
NOTE
To
replace the filter assembly on
body-cover by taking
serials TC-95j thru TC-7,00? and
air filter
TE-1 thru TE-JSI, a vacuum source indicator
located in the vacuum gage, will indicate failure
of either vacuum pump,
machine
On
airplane
the instrument,
out
remove
the
the four fiIlister-he~d
screws. Lift out the snap ring which holds the filter
place, remove the filter, and replace it with a new one.
Replace the air filter body-cover and gasket, securing them
with screws. If the air filter body-cover is not used. the filter
may be removed by lifting the snap past the four protective
in
lugs.
CENTRAL GYRO AIR FILTER
(TC-1014 thru TC-2002; TE-208 thru
SURFACE DEICER SYSTEMS
TE-451)
installed for dual instruments) is
incorporated in the instrument lines to protect the instruments
from dust and other foreign particles.Tnis filter(s) is a sealed
A central air filter
panel and
should be replaced every 500 hours (or less during operation
in dusty or heavy smoke conditions). Replacement may be
unit mounted
made
Locate the filter(s), mounted
a.
panel
at
the base of the
Remove the
b.
remove
bracket behind the instrument
follows:
as
control
on a
centrally
behind the
panel.
wing nut at the
base of the
housing and
the filtrr from the bracket.
c.
removing
d.
reversing
Disconnect the hoses
at
the top of the filter
the attach clips.
Discard the old filter and Install
the above noted
a new
filter
by
by
procedure.
CLEANING THE SUCTION RELIEF VALVE SCREEN
(TC-1 thru TC-2002; TE-1 thru TE451)
cleaned depends on the conditions
airplane is tlown. Should the valves need
adjusting, especially to lower the vacuum. the screen should
be cleaned and the setting recfiecked before redduusting. The
How often the
LIGHTWEIGHT AUTOMATIC
SURFACE OEICER SYSTEIW
The
following description applies to deicer systems utilizing
applicable also to systems
incorporating Tavco control valve nssemblies. with the
Goodrich control valves, but is
should be washed in Stoddard solvent, or
cleaner, then blown dry with high pressure air.
screen
a
similar
operation and air filtering
separately.
which will be discussed
The
principle components of the deicer system are:
Lightweight rubber and fabric pneumatic deicer boots
cement-b~nded to the wing and empennage leading edges;
the two engine-driven vacuum pumps which provide air
pressure for deicer boot inflation and vacuum for deicer
boot deflation; an electric timer forward of the instrument
panel which actuates a solenoid operated combination
overboard-pressure relief control valve in each engine
nacelle; pressure sensitive shuttle valves to control the Flow
of air to and from the boots: a three position switch to control
the
operation of the
timer (nnd hence the deicer system); and
irzr
Fi~ures
the necess~ry plumbing and wirin,o componenrs
11-~, 11-5 and the wiring diagram in Section 1~).
Normally,
being
placed
of the air filter in the gyro instruments mnv
be accomplished without removing the instrument from the
vacuum pumps apply vacuum
all times, except when the boots are
innated. When the deicer system control switch is
at
in either the ~IIANUAL
or .I\UTOi~IAnC position.
energizes the combination overboard-pressure
relief valves. the energized control valves port pressurized air
the timer
the pressure sensitive shortie valves which, in turn, shut off
vacuum normnllv applied to the boots and allow
the
pressurized
of 15
replacement
the engine-driven
deicer boots
to the
to
REPLACING GYRO INSTRUMENT AIR FILTERS
~C-l thru TC-2002; TE-1 thru TE451~
11-4
of control valve
exception
provisions,
screens are
under which the
The
(PUMP-DRIVEN:
to
18
air
to
psig
inflate
the boors. h deicer system pressure
by the pressure: relief function
is maintained
of the control valves. When the control valves are
de-energized by the timer, the shuttle valves port the boot
E10
BEEOHCRAFT
BARON 55 AND 58
SHOP MANUAL
VACUUM REGULATOR
I
C
L--dl´•-PLI
L´•
r
LI r’
K VALVE
I
I-
Y
CHECK VAL
DIRECTIONAL
GYRO
MSTRUMENT
SELECTOR
HORIZON
VACUUM GAGE
I~--e
B
VACUUM
vAcvvb
REGULATOR
EFFECTIVE TC-I THRU TC-190
REGULATOR
VACUUM,T
PUMP c~
VACUUM
PUMP
L
\I’
ss~
~O´•
CHECK
VALVE
CHECK
VALVE
kCUvM
REGULATOR
VACUUM \3~
GAGE
B
I
I
I
VACUUM
REGULATORI
DII-IECTIONAL
GYRO
HORIZON
GYRO
--ir
EFFECTIVE TC-191 THRU TC-909 EXCEPT TC-846
I
VACUUM
VACUUM
’ry
mJMp~x
17,mUMP
YLr
YI~
~t d-;
3
1’
p
rmd afteri
TC-1
TC-1 thru TC-190 TE-1 tnru TE-451
VACUUM REGULATOR ADSUSTMENT
VACUUM PUMP
55-194-29
Figure 11-1.
E10
Vacuum
System (TC-1 through
TC-909 except TC-846. TE-1 through TE451)
11-5
BEECHCRBFT
BARON 55 AND 58
SHOP MANUAL
VACUUM GAGE
CHECK
VALVE
VALVE
VACUUM
REGULATOR
I
I
I
I
vAcvv~i
I
I
REGULATOR
DIRECTIONAL
GYRO
GYRO
HORIZON
i~VACUUM
VACUUM
~PUMP
PUMP/\’
\(L\´• I
Figure 11-2,
Vacuum
System(TC-846,
TC-910
through TC-1013,TE-? through TE-207)
VACUUM GAGE
CHECK
VALVE
1
I
1
I
I
I
VACUUM
‘t,
1
DIRECTIONAL1~71I-+
REGULATOR
GYRO
CYRO
HORIZON
GYRO
CHECK
VALVE
YACUUM
REGULATOR
DIRECTIONAL
GYRO
O
HORIZON
IVACUUM
_C_PUMP
ilr
AIR
Iti=,
FILTER
VACUUM
PUMP
DUAL ~NSTALLATION
I
55-194´•-30
Rgure
11-6
11-3. Vocuum
System (TC1014
thru
TC-2002, TE-208 tt~ru rr-451)
510
BEECHCRATT
BARON 55 AND 59
SHOP MANUAL
Vertical Stabilizer Boot
R. Il. Horizontal
L. H. Horizontal
Stabilizer Boot
Stabilizer Boot
Valve
rl~or
To H-14
Autopilot
Control Valve
Solenoid
Valve
Filter
\I‘.i~i
:~I
Separator
I
I:Pressure
VOil Separator
To Vacuum
L
R. H.
Wing
Boot
Control
41~ve
Overboard
I
_J;
Pump
Airplanes
Controll
I
wfth H-14
Oil
Separator
Oil
Separator
Relief Valve
Vent
Autopilot Installation
L´• H´• Wing Boot
Valve
Clt
Air Filter’
boverbo~rd
Overboard
Vent
i
X
/air Filter
Oil Separator
O
I
00il Separator
Vacuum Pum
Vacuum
VIIVIIY,
Pump
Effective TC-870 thru TC-?002. ~E-l thru TE-~j 1
TC-483, TC-499. TC-602, TC-616, TC-657, and TC-690 only
Effective TC-859 thru TC-2002. TE-I thru TE-451
55-193-36
Figure
E10
11-4.
Lightweight
Automatic
(Pump-Driven)
Surface Deicer with Tavco Valves
11-7
BEECHCRAF~
BARON 55 AND 58
SHOP NIANUAL
YertlcalStabiltter
Boot
H-14
Autopilot
Air Filter
I
R. H. Horizontal
Stabilizer Boot
L. N. Horizontal
Stabilizer Boot
Separator
Overboard Vent U
I´•
Pressure Rellet
To Overboard
~d
Valve"
Vent
X
si
’Overboard Vent
I
Overboard Vent
!Pressure
Solenoid
valve
Control ValveerY
Air
Fllter(
~C
Shuttle Valve
IO11
R. H.
Wing
Separator
1
I
5
Valven
r
I
1
I
Boot
Solenoid
Valve
AirFLlter(
I
Shuttle
I
8i
Control Valve
I
rl
RellelValve
f
011
Selnrator
I
L. H.
Wing
Boot
Pressure
Gage
Vacuum
Pump
Vacuum
~Airplanes
’Omitted
with H-14
on
Airplanes
Autopilot
Pump
Installation
with H-14
Autopilot
Installation
Effrctive TC-859 thru TC-2002, TE-1 thru TE-UL
55-193-39
Figure
11-8
11-5.
Automatic (Pump-Driven) Surface Deicer
with Goodrich Valve Assemblies
Lightweight
System
E10
BEECHCRAFT
BARON 55 AND 58
SHOP IMANUAL
the control valves: system
inflating air overboard through
vacuum is then reapplied to the
boots.
control
operated
the electric timer the solenoid
Through
simultanlously;
therefore, the system is described as a ’’single-inflation"
type. Since the control valves operate simultaneously and are
valves
cause
positive
in
all of the boots
positioning
from
to
be intlated
"dump" to "deicer pressure"
engine-driven vacuum
operation of the deicer
the system will operate with one
pump inoperative, which permits
system
on one
a second oil separator is plumbed between each rngine
oil separator and control ~cllve assembly: a drain line from the
second oil separator connects with the overboard vent line to
convey the condensed oil vapor overboard. Effective
only,
TC-870. TE-1 through TE-jSI,
plumbed
corresponding
Each Tavco control valve
Both MANUAL and AUTOMATIC positions of the deicer
immediately inside the
are momentary. Momentary engagement of the
AUTOMATIC position will automatically inflate the deicer
boots for five to eight seconds before they resume the vacuum
the H-14
hold-down condition. The MANUAL position will intlate
the boots only while the switch is held in engagement; when
released, the boots will
the switch is
return to
the
micron filter is
0.3
oil
and
separator
oil vapor.
Condensed oil vapor is conducted overboard through a drain
line connected to the overboard vent line.
control valve
engine.
switch
a
engine
assembly
each
between
the
during
Autopilot.
this
contains
assembly
a
screw
port. On airplanes equipped ~’ith
vent
screw
is removed and pressure
is utilized for
deicing cycle
to remove
powering the autopilot
servos.
SYSTEhl CHECKOUT
vacuum
Control
hold-down condition.
operation
Check control valve
The oil separator in each engine accessory section recovers
oil in the pump output air; the oil is then returned to the eneine
outlet of each
sump. An air filter is connected to the pressure
control valve to remove foreign particles and any remaining
oil from the deicer boot inflatin~ air. The deicer system also
contains a gage in the cockpit to register system pressure and
the deicer
a standard reset type circuit breaker to protect
in the AL’TOMA~IC
system elrctrical circuit,
i’click"
ii.
Turn
i.
on
the
battery
follows:
as
master
switch.
the deicer system switch
Momentarily place
position.
The control valve solenoid should be actuated
seven seconds as evidenced by an audible
3.
for
immediately
"click" at the beeinning and
can also be detected
at
the end of the
by placing
cycle.
the hand
The
the
on
solenoid.
b.
SYSTEMS INCORPORATING
TAVCO CONTROL VALVE ASSEMBLIES
If
control valve does not function,
a
a
When the deicer system three- position
solenoid-operated pilot valve builds up pressure against the
pressure-vent shuttle spool, causing the boots to be
reaches
the
npproximately
one
port and the
boot pressure is
vacuum
pressure continues to increase until regulated
reached. The pressure relief valve is an inteoral part of the
control valve
de-energized,
at
the
a
test
light or other suitable test
place the deicer switch in the
the connector and
AUTOMATIC position.
If the test
3.
complete circuit,
equipment
does
not
indicate
check the circuit from the timer
re,
a
the
ground.
Replace defective timer component (holdinX
time-delay), if necessary.
solenoid connector
to
or
Use an ohmmeter to check the solenoid for an
If
the solenoid circuit is open, replace the
circuit.
open
control valve.
the boots to evacuate.
c.
Two small lines, pilot pressure and priority pressure,
plumbed between the valve assemblies in the nacelles allow
of the system on one engine by using pressure from
operation
the valve for the
operative engine to operate the
circuit is
On Goodrich control valves
Remove the
i.
only,
if the solenoid
following check:
solenoid safety wire and unscrew
satisfactory perform
the
solenoid.
shuttle in the
valve.
CAUTION
Each control valve
assembly incorporates
a
filter to
remove
from the system. On airplanes
TC-616,
TC-657, and TC-690
TC-483, TC-j99, TC-602,
oil and any
EIO
Attach
2.
equipment to
relay
opposite
connector
4.
the shuttle returns to the
’’dump" position. When the remaining boot pressure lowers
to 1 to 1.5 psi_g, the ball poppet opens to the vacuum pen,
permitting
as
solenoid.
assembly.
After the solenoid is
the electrical
Unplug
i.
switch is activated,
pressurized. When the pressure
pSi_g, a ball poppet closes off
proceed
follows:
foreign particles
Do
not
lose the steel hex actuator
pin or the
valve
poppet.
11-9
BEECHCRAS~T
BARON 55 AND 58
SHOP MANUAL
2.
Reattach the
connectorto
the solenoid, insert
b.
Tavco Control Valve Installation.
the hecx actuator
pin into the solenoid, and actuate the deicer
switch. If the pin is not ejected from the solenoid, replace the
After each 100 hours of
control valve.
cover on
engine operation. remove the filter
assembly to dispose of residual
each control valve
oil in the filter.
Air Leakaee Test
Control Valves
a.
Cap
b.
Connect
the overboard port of the control valve in
either the left or right nacelle.
the inlet port of the
control valve. A minimum inlet pressure of 18 to 20
capped
psi,o is required
for the
Install
c.
a source
a
of clean air
test,
pressure page in the air line
to
observe
system pressures.
Apply 18 psig pressure to the system and, with a
hand operated valve, trap the pressure in the deicer system,
Observe the system for leakage; the leakage rate
e.
should not exceed a pressure drop of 4.0 psig per minute,
f.
Remove the test equipment, lubricate all threads,
and replace all system components.
d.
Vacuum Relief Valve
a.
After
See Vacuum
approximately
the valve
stick. To determine if the valve poppet is sticking, perform
the checks outlined in System Checkout, Control Valves. If
the solenoid ejects the hex actuator
pin (Step e, 2), proceed as
follows:
i.
Remove the solenoid electric:ll connector.
2.
Remove the valve poppet.
Adjustment
System.
operation,
100 hours of en~ine
poppet and internal lining of the control valve may become
coated with a film of dried oil, causing the valve poppet to
NOTE
For proper operation of the deicer system the
vacuum relief valves must be adjusted to provide
vacuum.
Goodrich Control Valve
to
this Section.
airplane
adequate
if adjustment is
It may be necessary to apply slim nose pliers to
the pin projection in order to pull the poppet from
the valve.
required.
OPERATION CHECK
3.
poppet with
a.
With bath
engines operating
cruise rpm,
the deicer switch in the AUTOMATIC
momentarily place
position; the deicer
3.
at
boots should inflate for five to
few seconds; the deicer boots should inflate
and remain inflated while the switch is retained in the
MANUAL position. Check for correct system pressure,
c.
Release the deicer switch,
permitting
it
b.
positionl
vacuum
hold-down condition,
d.
Repeat Steps "a" through "c"
operating individuallq´• at cruise rpm.
with each
hydrocarbon-type
a
Assembly
valve poppet may be caused by a film of dried
the poppet and the interior of the valve. The valve may
be cleaned as follows:
Disconnect the valve assembly and remove it
I.
oil
on
from the
airplane.
Force
a
hydrocarbon-type
commercial
solvent into the inlet port of the valve
operating the solenoid several times.
assembly
while
engine
WARNING
Air Filters
Observe the normal
for this type of
safety precautions required
operation.
Goodrich Control Valve Installation.
3.
Examine the filter discs after each
Reinstall the valve
assembly.
100 hours of eneine
operation and clean if oil has accumulated in the filter
housing. For a cleaning agent use a commercial hydrocarbon
type solvent such as naphtha, petroleum ether, or gasoline;
kerosene-type distillates should be avoided.
11-10
safety
Sticking of the
COMPONENT MAZNTENANCE AND REPLACEMENT
a.
solvent.
Reassemble the valve and reinstall and
Tavco Control Valve
to return to
the deicer boots should deflate and reach
the OFF
clean the control valve bore and
eight
is within the green are on the deicer system pressure gage.
Place the deicer switch in the MANUAL position
b.
a
Thoroughly
commercial
the solenoid.
seconds, then deflate and reach a vacuum holddown
condition. During inflation, check to see that system pressure
and hold for
a
Timer
The timer consists of a holding
relay
Defective components may be
and
a
replaced
time -delay de~´•ice.
as
required.
510
BEECHCRAFT
BARON 55 AND 58
SHOP MANUAL
assembly,
Shuttle Valves
No field maintenance is recommended
Defective valves should be
Corporation
for
shuttle valve is
sent
to
or
Lack of
Component Replacement
authorized.
No component maintenance other than that described in this
manual is recommended.
repair or replacement. Since the Tavco
integral part of the complete control valve
TROUBLESHOOTING SURFACE DEICER
i.
shop
(PRESSURE SYSTEM) (Prior
PROBABLE CAUSE
adequate vacuum
completely.
inspection.
Seech Aircraft
an
INDICATION
the entire unit must be submitted for
a.
Clogged
lines.
b.
Leaking
lines.
c.
Pressure
to TC-2003
TE-452)
REMARKS
detlate boots
needs
2.
Lack of
to
adequate air pressure
completely,
regulator
adjustment.
d.
Distributor valve is defective.
a.
Clogged
lines.
b.
Leaking
lines.
c.
Pressure
inflate boots
needs
3.
valve
Boots fail to inflate with switch
in either AUTO
regulator
adjustment.
valve
d.
Distributor valve is defective.
a.
Blown
a.
Defective control
a.
Defective timer
relay.
a.
Defective timer
relay.
or
defective fuse.
MANUAL
or
position.
4.
5.
Soots fail
to
in AUTO
position.
inflate with switch
Boots inflate with switch in
AUTO
position,
but deflate
when
instantaneously
spring loaded
off position.
h.
13 to
position.
Boot inflation time either
or
less than 5
to
more
8 seconds with
switch in AUTO
E10
over
to
seconds with switch in
AUTO
7.
the
switch returns
Boots fail to inflate
15
relay.
a.
Timer
relay
adjusted.
not
properly
position.
11-11
DEEOHORAFF
BAFION 55 AND 58
SHOP MANUAL
LIGHTWEIGHT SURFACE DEICER SYSTEM
(RESERVOIR TYPE)
COMPONENT TEST AND ADJUSTMENT
Control Cables
a.
i.
The air
supply
attached to the reservoir air
valve control cable should be
supply
operating lever closes completely
short against the cable mounting
2.
to
cycling
the
The
valve
cycling
so
valve
so
that the valve
without the cable
stopping
in the cabin.
control cable should be attached
that the control
arm can
operate
to
the
valve. The cable handle in the
limits of the cycling
position should have a ’/4 inch cushion from the cable
mounting in the cabin to insure the cycling valve is in the
fully closed position.
extreme
"IN"
b.
Air Pressure
Regulator (See Figure 11-6)
will not register unless the air supply valve is
air
the
With
supply valve in the open position observe
open.
the gages. If the gages do not correspond to the followin_9
table, reset the regulator to apree with this table.
i. Lock Nut
2. Pressure Adjusting Screw
Regulator gages
INLET PRESSURE
Figure
11-6. Air Pressure
55-190-13
Regulator
REGULATED PRESSURE
(PSI)
(PSI)
3000
17.0
2500
18.0
2000
19.0
1500
20.25
1000
21.5
750
1,2.75
500
21.0
750
7,5.5
The pressure regulator may be adjusted by loosening the
locknut on the pressure regulator and turning the screw
clockwise to decrease pressure and counterclockwise to
increase pressure.
c.
Cycling
Valve
5 5-190-14
(See Figure 11-7)
i.
"Pop-Ofr’
4.
valve mechanism base.
Figure
11-12
Adjusting Ring
2. Detent
Cycling Valve Control Arm Adjustment.
Ca) Adjustment for all possible variations in
control
arm
the
assembly is accomplished by the addition or
removal of laminated shims between the upright supporting
the control arm and the angle attaching the upright to the
i.
Pressure
3. Cotter Pin
"Dog"
5. Shim Location
11-7.
Cycling
Valve
E10
BEECHCRAFT
BARON 55 AND 58
SHOP MANUAL
(b) With the valve shaft actuated and locked
in the detent, the control arm is properly adjusted only when
the "dog" which operates the valve shaft will:
(I)
Engage 1/64 to 1/32
an
inch
on
PNEUMATIC PRESSURE SYSTEM-IPISTRUMENT~
(TE-452
after)
and after; TH-1 and after; TC-2003 and
the
shaft and then:
NOTE
Slide past the shaft without driving
the shaft beyond and out of the detent.
(c) The adjustment of the mechanism is
accomplished by loosening the fasteners between the
previously described upright and angle, then adding or
(2)
operate these components in the
laminated shim stock.
removing
If the
Airplanes with four (or more) air-driven gyros
and an air-operated autopilot installed should be
equipped with high capacity air pumps to safely
single-engine operation.
capacity must be used as
event
A pump of the
of
same
replacement.
a
"dog"
engages too far on the shaft or drives the shaft
the
add shims until the mechanism is properly
detent,
past
adjusted. If the idog" does not cause the valve shaft to
engage in the detent, remove shims until the valve shaft
engages in the detent
(d)
The valve
valve should be
reservoir
functionally
package.
2.
The
satisfactorily.
Cycling
operating
mechanism and
tested with pressure from the
through the
of the
Valve
Adjustment.
properly adjusted when the
low pressure,oage on the regulator reads 15 to 17 psi at the
time the valve shaft automatically returns to its normal
position,completing the deicing cycle. This is known as the
’’pop-off’’ pressure. The low pressure,oage on the regulator
will show a higher value after the valve completes the deicing
cycle. This higher value is the set pressure of the regulator.
(b) The value is adjusted by rotating a ring
on the valve located directly below the top plate on the
(a)
pneumatic pressure system supplies air to operate the
pressure-driven instruments and (if installed) the deice and
autopilot systems. Pressure system operation is by air intake
The valve is
working end of the valve. The cam action of the interior of
ring increases or decreases the ’’pop -off’’ pressure as the
ring rotates.
(c) To adjust the "pop-off" pressure of the
ambient air (foam rubber) filters located forward
engine baft7e an each engine. The filtered air is
then passed through the two engine-driven dry air pumps to
the pressure regulators located on the topside of each nacelle
rear
aft of the firewall. The regulators reduce the pressure of the
air from the pumps to a
level then pass it on through a
prceset
pair
of inline system filters to a pressure manifold. The
pressure manifold is located aft of the front spar, behind the
upholstery panel in the LH sidewall. Air is then distributed
from the manifold forward throu´•h an adjustable orifice
(TE-452 thru TE-767) or a regulator valve (TC-2003 and
after; TE-768 a!ld after; TH- I and after) to the instrument
panel. Air is plumbed off the manifold to operate ~if installed)
the deice and
autopilot systems.
this
valve:
(1)
adjusting ring
to
cotterpin locking
"pop-off" pressure
regulator.
(3)
again
body.
Cycle the
on
The intake filters
valve and observe the
the low pressure gage of the
Determine from the
pressures, the direction of the adjusting
decrease the "pop-off" pressure,
(5)
so
that the
"pop-off"
(6)
valve
E10
body
AIR FILTER
located
are
on
the forward side of each
baffle. The foam type should be removed each
100 hours (or sooner depending upon conditions) and washed
engine
rear
in solvent and blown
adjusting ring, recycle
"pop-off" pressure.
Rotate the
observe the
(3)
(AMBIENT)
the
the valve
(9)
the valve and
Remove the
PRESSURE SYSTEM INTAKE
REPLACEMENT
Set the
ring
adjusting
to
rinrr
pressure is from 15-17
Relock the adjusting
with the cotter
pin.
"pop-off"
increase
on
or
the valve
psi.
ring
to
the
dry with low pressure shop air. On
serials TE-937 and after. TC-2003 and after, TH-373 and
after and earlier
airplanes
which have
complied
with
BEECHCRAFT Service Instruction No. 0581-194, the
intake filters (Fi_eure 11-8) should be replaced annually,
every 300 hours (or sooner depending upon conditions) or
whichever comes first. This filter element should not be
subjected to solvent
Always reinstall the
and must be
tilter
cover
replaced
with the
if this
occurs.
opening facing
down.
11-13
BEECHCRAFT
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING LIGHTWEIGHT SURFACE DEICER
INDICA TION
i.
Deicers do
flate
PROBABLE CA’USE
inflate,
not
or
in-
a.
slowly.
Control cables
or
not
not
(RESER~OIR-TYPE)
REMARKS
connected
a.
fastened to the valves
Inspect cable connections to the L´•alves
tightness and proper adjustment.
for
tightly.
b.
Mechanical
interference
of
b.
Correct interference
Charge
problem.
cables
c.
Reservoir empty,
c.
d.
Shut-off valve not open,
d.
Check shut-off valve control
proper
e.
Regulator
set
for too low
reservoir.
cable for
adjustment.
a
e.
Reset
or
f.
Check c).cling control cable for proper ~td
regulator.
pressure.
f.
g.
Cycling valve not operating
not completely engaged.
Piping,
lines blocked
j,,tment.
not
g.
operating
a.
or
Blow
out
lines and
~nspect
connections.
connected.
Deicers do
f)ate
not
deflate,
or
de-
a.
slowly,
Cycling
valve
not
properly.
Check cycling control cable for proper aJjustment 3nd possible mechanical interfelence.
b.
Piping, lines blocked
not
b.
at
c.
vac-
d.
Start right engine
tem malfunction.
a.
Check
or
Blow
out
lines and
inspect
connections.
connected.
c.
Check valve malfunctions
cycling
d.
valve assembly,
Right engine
uum supply
not
to
running
aid deflation
Observe check valve. Unplug outlet, repair or replace check valve if defective.
or
correct vacuum sys-
and hold down is not avail-
able.
3.
Deicer remains
inflated:
servoir drains
first
aotomatic
on
return
of
re-
a.
Improper tubing Fonnection.
cycle or
cycling
tubing
connections
to
cycling
valve.
valve does not function.
Regulator safety valve
ping under 30 psi.
5.
Shut-off valve does
complete
not
pop-
a.
Regulator safety valve impro-
perly
effect
a.
shut-off.
a.
Reset valve.
a.
Check
a.
Adjust the cycling valve "popoff"
set.
Shut-off valve actuating pin
does not drop free so as to let
actuating pin. replace
if defective.
the shaft inside the valve seat
completely.
h.
Cycling
turn
valve
automatic
re-
functions before deicers
a.
Cycling valve
ment.
out
of
ndjust-
pres-
sure,
fully inflated or inflation
cycle is longer than 5 to 9
are
seconds.
11-14
EfD
Qeechcraft
BARON 55 AND 58
SHOP MANUAL
PRESSURE SYSTEM IN-LINE FILTER
INSPECTION
AND
On
AND
(78-452
c.
AFTER, TH-I
AFTER, TC-2003 AND AFTER)
airplane
TH-372,
d.
serials TE-452 thru TE-936 and TH-1 thru
remove
both in-line filters from the system
by comparing the resistance
and check for obstruction
to flow with
source
a new
(max,
of 10
to
a dry, low-pressure air
accomplish this test. If the
a
filter removed from the air-
resistance to air flow in
plane exceeds that of a new filter by more than one
psi, the filter should be replaced. On airplane serials
TE-937 and after; TH-373 and after; TC-2003 and
after, the filter should be replaced annually, every 300
hours of service time or sooner depending upon oper-
ating
conditions. The filter must not be
solvents and must be
if this
replaced
subjected
to
occurs.
PRESSURE SYSTEM ADJUSTMENT
TH- I AND AFTER,
(TE-452 AND
TC-2003 AND
AFTER)
Adjustment of the pressure system components in a
specified sequence is given independently for each
configuration available. The following system headings will facilitate adjustments on a particular airplane.
BASIC PRESSURE SYSTEM
as
reading
each
test gage
10
the regulator) to obtain a
Hg on the gyro pressure indiengines operating at 2300 rpm.
screw on
After adjusting the orifice (regulator), the pressure
the test gages at the pressure regulators in the
nacelles should be rechecked with each engine operating individually at 2300 rpm. If the pressure on these
gages has been affected by the adjustment of the orifice (regulator), the regulators in the nacelles should
readjusted
to 5.0 +.5
psi.
With both engines operating at 2300 rpm, the difference between the pressure gages at the pressure
regulators in the nacelles should not exceed .5 psi.
f.
NOTE
If the requirements of this adjustment
procedure cannot be obtained, the complete system (including the check valves
on the manifold) should be checked for
leaks and/or restrictions; then any discrepancy should be repaired and the
system readjusted.
valve.
psij
g.
Remove the test gages from the
BASIC PRESSURE SYSTEM WITH 8-4, 8-5, OR
(Figureil-lO)
NOTE
at the "out" side of
Airplane serials TE-452 thru TE-767 are
equipped with a gyro instrument adjustable orifice. Airplanes TC-2003 thru
TC-2102, TE-763 thru TE-1133, and
TH-1 thru TH-935
are
equipped
with
a
gyro instrument regulator valve.
NOTE
Rotate the pressure regulator adjusting
screw clockwise to increase pressure
and counterclockwise to decrease pres-
airplane.
8-7 AUTOPILOT INSTALLATION
Operate one engine at 2300 rpm and adjust the
pressure regulator for that engine to obtain a reading
of 5.0 -c.5 psi on the test gage.
815
or
on
b.
sure.
adjustable orifice
e.
(INSTRUMENTS
regulator
(0
pressure regulator.
a
opposite
2. Tighten the check nut and recheck the gyro
pressure indicator to read in the green are with both
engines operating at 1500 rpm.
follows:
Airplane serials TE-452 thru TE-767 are
equipped with a gyro instrument adjustable orifice. Airplanes TC-2003 thru
TC-2102, TE-768 thru TE-1133, and
TH-1 thru TH-935 are equipped with a
Install
the
of 5.0 +.1 -.2 in.
cater with both
NOTE
a.
on
Loosen the check nut and rotate the orifice
1.
ONLY)
(Figure 11-9)
gyro instrument
step b
Locate the gyro instrument
body (adjusting
be
Adjustments may be accomplished
in
regulator valve (if installed) on the LH side of the airplane forward of the instrument panel, near the top of
the upholstery panel and adjust as follows:
filter. Use
psi)
Repeat the adjustment
airplane.
Side of the
a.
Install
a
b.
Install
tor
supply
(0-10 psi)
regulator.
test gage
each pressure
at the "out" side of
a test gage (0-10 psi) in the turn coordinaline. Refer to Figure 11-10.
11-15
BARON 55 AND 58
SHOP MANUAL
FILTER CARTRIDGE
MOUNT
h
IFOR REPLACEMENT ORDER P/N 09-14-1)
58-910021-1 COVER
NAS43DD3-24 SPACER
AN315-3R NUT
NUT
i
I
II
Ilj
IiI
i
1LTER
I
PiN936A10
LOCK
WASHER
BASE
N970-3 WASHER
L
AN960PD1716 WASHER
FILTER RETAINER
NUT AND WASHER
STD-IPO-19
Figure
11-16
11-8. Ambient Air Filter
Assembly (iJ2-5)
815
BARON 55 AND 58
SHOP MANUAL
ARROW INDICATES
DIRECTION OF
AIR FLOW
OUT
ADJUSTABLE ORIFICE
I r -1 h
REGULATOR
rf I’
II
(I
ii
r\
I
´•t~.
it
UIOVERBOARD
IGYRO ~L ~nlRECTION
llt~’_9RIZON
-il
7
11
GYRO
GYRO
DIRECTION
HORIZON
GYRO
""7
VENT LINE
I:
GYRO
~PRESSURE LINE
PRESSURE
INDICATOR
CHECK VALVE-~
MANIFOLD
L-
CHECK VALVE
FILTER
TEST GAGE
PRESSURE REGULATOR
PUMP
FILTER
55-194-28
Figure
E15
11-9. Pressure
System,
Basic
(Instruments only)
11-17
Qeechm~aft
BARON 55 AND 58
SHOP MANUAL
ARROW INDICATES
DIRECTION OF
AIR FLOW
OUT
ADJUSTABLE ORIFICE
REGULATOR
VENT LINE
I r -Ihr
1
-\~-----7
II
II
II
OVERBOARD
II
/nIRECTION
I I GYRO
IIHORIZON
L’--r
PRESSURE LINE
/GYRO
GYRO
DIRE CTION
HOR IZ ON
GYRO
---------;1
TEST
GAGE
J
GYRO
~J
PRE SSURE
INDICATOR
111-
TURN
I
AUTOPILOT
C OORDINAT OR
L
MA STE R
~h
CHECK VALVE’
"MANIFOLD
VA LVE
CHECK VALVE
FILTER
TEST GAGE
PRESSURE REGULATOR
PUMP
FILTER
55-191-8
Figure
11-18
11-10. Pressure
System,
Basic with 8-4, 8-5
or
8-7
Autopilot
Installation
815
43eechcraft
BARON 55 AND 58
SHOP MANUAL
Operate one engine at 2300 rpm and adjust the
pressure regulator for that engine to obtain a reading
of 5.0 +.O -.5 psi on the test gage in the turn coordinator supply line with the autopilot ON. Normally a pressure of 6.5 psi on the test gage at the pressure regulater is sufficient to obtain the 5.0 +.O -.5 psi reading
c.
at the turn coordinator.
should the
7.0
reading
Under
no
at the pressure
BASIC PRESSURE SYSTEM WITH H-14
AUTOPILOT
(Figure
NOTE
Airplane serials TE-452 thru TE-767 are
equipped with a gyro instrument adjustable orifice. Airplanes TC-2003 thru
TC-2102, TE-768 thru TE-1133, and
TH-I thru TH-935 are equipped with a
gyro instrument regulator valve.
circumstances
regulator exceed
psi.
NOTE
Rotate the pressure regulator adjusting
clockwise to increase pressure
and counterclockwise to decrease presscrew
sure.
a.
Install
Repeat step c on
the
opposite side
of the
airplane,
Locate the gyro instrument adjustable orifice or
regulator valve (if installed) on the LH side of the airplane forward of the instrument panel, near the top of
the upholstery panel and adjust as follows:
e.
Loosen the check nut and rotate the orifice
1.
body (adjusting screw -of the regulator) to obtain a
reading of 5.0 +.1 -.2 in. Hg on the gyro pressure indicator with both engines operating at 2300 rpm.
2.
Tighten
a
b.
Install
a
(0-15 psi)
regulator.
test gage
each pressure
test gage
(0-10 psi)
at the "out" side of
in the
autopilot
sup-
at the "out" side of the pressure manifold.
ply line,
d.
11-11
Operate one engine at 2300 rpm and adjust the
pressure regulator for that engine to obtain a reading
of 7.5 ~.5 psi on the test gage in the autopilot supply
line with the autopilot ON. Normally a pressure of 8.5
psi on the test gage at the pressure regulator is sufficient to obtain the.5 ~t.5 reading in the autopilot supply line. Under no circumstances should the reading at
the pressure regulator exceed 9.0 psi.
c.
NOTE
Rotate the pressure regulator adjusting
clockwise to increase pressure
and counterclockwise to decrease pres-
the check nut and recheck the gyro
are with both
screw
pressure indicator to read in the green
engines operating at 1500 rpm.
sure.
the gyro pressure orifice (regulator), the pressure on the test gage in the turn coordinator supply line should be rechecked with each engf.
After
ine
operating individually
on
adjusting
at 2300 rpm. If the pressure
the test gage has been affected by the adjustment
(regulator), the regulators in the nacelles
of the orifice
should be
readjusted
as
specified
in
steps
c
and d.
g. With both engines operating at 2300 rpm, the difference between the pressures on the test gages at
the pressure regulators in the nacelles should not
exceed .5
psi.
NOTE
be checked for leaks and/or restrictions;
then repair the discrepancy and readjust
the system.
Remove the test gages from the
815
Locate the gyro instrument adjustable orifice or
regulator valve (if installed) on the LH side of the air-
plane,
airplane.
near
the top of the
panel, and
the instrument
upholstery panel forward
adjust as follows:
of
Loosen the check nut and rotate the orifice
reading of 5.0 +.1 -.2 in. Hg on the
gyro pressure indicator with both engines operating at
1.
body
to obtain a
2300 rpm.
2.
Tighten the check
nut and recheck the gym
pressure indicator to read in the green
engines operating at 1500 rpm.
are
with both
After
adjusting the gyro pressure orifice (regulathe
tor),
pressure on the test gage in the autopilot
line
should be rechecked with each engine
supply
e.
If the requirements of this adjustment
procedure cannot be obtained, the complete system, including the check valves
and the gaskets in the manifold, should
h.
d.
operating individually at 2300 rpm. If the pressure on
the test gage has been affected by the adjustment of
the orifice (regulator), the regulators in the nacelles
should be
f
readjusted
as
specified
in
steps
c
and d.
With both
engines operating at 2300 rpm, the difference between the pressures on the test gages in
the nacelles should not exceed .5 psi.
11-19
Qeechcr~ft
BARON
55 AND 58
SHOP MANUAL
ARROW INDICATES
DIRECTION OF
AIR FLOW
OUT
ADJUSTABLE ORIFICE
REGULATOR
Tr~" h-~-----=
OVERBOARD
GYRO
HORIZ ON
GYRO’ LDIRECTION RI
IU
GYRO
HORIZ ON
L,
L-=2=--=
DIRECTION
GYRO
--i)
Lrrl
VENT LINE
II
PRESSURE LINE
TO H-14 AUTOPILOT
TEST GAGE
zJ_j
GYRO
PRESSURE
INDICAT OR
L
CHECK VALVE"
MANIFOLD
L-
CHECK VALVE
FILTER
ST GAGE
PRESSURE REGULATOR
PUMP
FILTER
55-191-7
Figure
11-20
11-11. Pressure
System,
Basic with H-14
Autopilot
Installation
E15
aeechcraft
BARON 55 AND 58
SHOP MANUAL
NOTE
adjusting the gyro pressure orifice (regulathe
tor),
pressure on the test gage in the nacelles
should be rechecked with each engine operating individually at 2300 rpm. If the pressure on the test gage
e.
If the requirements of this adjustment
procedure cannot be obtained, the complete system, including the check valves
and gaskets in the manifold, should be
After
has been affected
by the adjustment of
regulators in the nacelles
specified in steps d and e
the orifice
(regulator),
readjusted as
should be
the
checked for leaks and/or restrictions;
repair any discrepancy and readjust the
system
NOTE
Remove the test gages from the
g.
airplane.
requirements of this adjustment
procedure cannot be obtained, the complete system, including the check valves
and the gaskets in the manifold, should
If the
BASIC PRESSURE SYSTEM WITH DEICER
I (Figure
11-12
Install
a.
each
a
test gage
Operate
b.
(0-20 psi)
at the "out" side of
be checked for leaks and/or restrictions;
then repair any discrepancy and readjust
the system.
two-stage pressure regulator,
one
engine
at 2300 rpm and
adjust the
two-stage pressure regulator for that engine
as
fol-
f.
Remove the test gages from the
airplane.
lows:
Adjust the low-pressure section of the regulator (section with solenoid) to obtain a reading of 7.5
~.5 psi on the deicer pressure gage with the deicer
system OFF. A pressure of 9.0 psi on the test gage in
the nacelle should be sufficient to obtain the reading
of 7.5 ~.5 psi on the deicer pressure gage.
1.
Adjust the high-pressure section of the regulator (section without solenoid) to obtain a reading of 16
to 19 psi on the deicer pressure gage with the deicer
system ON. A pressure of 17 to 20 psi on the test
2.
gage in the nacelle should be sufficient to obtain the
reading of 16 to 19 psi on the deicer pressure gage.
c.
Repeat step
b
on
the
opposite side of the airplane.
NOTE
BASIC PRESSURE SYSTEM WITH DEICER AND
8-4, 8-5, OR 8-7 AUTOPILOT
(Flgure 11-13)
Install a test gage (0-20 psi) at the "out" side of
each two-stage pressure regulator.
b.
tor
adjust
1.
airplane
as
Rotate the pressure regulator adjusting
clockwise to increase pressure
and counterclockwise to decrease pres-
the LH
forward of the instrument
panel
follows:
Loosen the check nut and rotate the orifice
body (or adjusting screw on the regulator) to obtain a
reading of 5.0 +.1 -.2 in. Hg on the gyro pressure indicater with both engines operating at 2300 rpm.
2.
Tighten
the check nut and recheck the gyro
are with both
pressure indicator to read in the green
engines operating at 1500 rpm,
515
in the turn coordina-
screw
d.
Locate the gyro instrument adjustable orifice (TE452 thru TE-767 or the regulator valve (TC-2003 thru
and
(0-10 psi)
NOTE
sure.
side of the
test gage
Operate one engine at 2300 rpm and adjust the
low-pressure section of the two-stage pressure regulater (section with solenoid) to obtain a reading of 7.5
~´•5 psi on the deicer pressure gage with the deicer
OFF. A pressure of 9.0 psi on the test gage in the
nacelle should be sufficient to obtain the 7.5 ~t.5 psi
reading on the deicer pressure gage.
Rotate the pressure regulator adjusting
clockwise to increase pressure
and counterclockwise to decrease pres-
on
supply
a
line.
c´•
screws
TC-2102, TE-763 and after, TH-1 and after)
Install
sure.
d.
Repeat step
c on
the
opposite side of the airplane.
Operate both engines at 2300 rpm and adjust the
autopilot pressure regulator to obtain a reading of 5.0
+´•O -´•5 psi on the test gage in the turn coordinator
supply line with the autopilot ON and the deicer OFF.
The autopilot pressure regulator is located in the nose
baggage compartment or under the pilot’s seat aft of
e.
the main spar.
Operate one engine at 2300 rpm and adjust the
high-pressure section of the two-stage pressure regulater (section without solenoid) to obtain a reading of
f.
11-21
aeechc~i
BARON 55 AND 58
SHOP MANUAL
ARROW INDICATES
DIRECTION OF
AIR FLOW
OUT
REGULATOR
ADJUSTABLE ORIFICE
II
!!II
1
II
II
\II
X
\IIOVERBOARD
LGYRO
LDZRECTIONLI
IIHORI[ZON
IL
GYRO
HORIZ ON
DIRECTION
GYRO
rrrr_lr=
I
L~
VENT LINE
PRESSURE LINE
DEICER PRESSURE GAGE
TO DEICER SYSTEM
GYRO
PRE SSURE
INDICATOR
I
CHECK VALVE"
LN,ANIFOLD
LCHECK VALVE
FILTER
TEST GAGE
I-
-11-
TWO-STAGE
PRESSURE REGULATOR
L
0.
’-I
O
I
PURr,
FILTER
55-192-7
Figure
11-22
11-12. Pressure
System,
Basic with Deicer Installation
515
Qeechc~ft
BARON 55 AND 58
SHOP MANUAL
ARROW INDICATES
DIRECTION OF
AIR FLOW
OUT
ADJUSTABLE ORIFICE
REGULATOR
VENT LINE
I
z-,
c
II
II
I i
GYR
IIHORIZON
"--1
i\.
OVERBOARD
I)
r------1!
I
PRESSURE LINE
LGYRO
LDIRECTION
HORIZON
GYRO
DIRECTIONIII
GYRO
II
TO B-5P
IIAUTOPILOT
ii
TEST
GAGE
B-5P
L~
C1~ AUTOPILOT
MASTER
PRE SSURE
II
II
II
-rrREGULs~TOR
TilRN
VALVE
COORDIN~TOR
II
~JJ
GYRO
PRESSURE
INDICATOR
TO DEICER SYSTEM
DEICER PRESSURE INDICATOR
-CCHECK VALVE
MANIFOLD
L--
CHECK VALVE
E"ILTE R
TEST GAGE
TWO-STAGE
PRESSURE REGULATOR
O
O
PUMP
FILTER
55-192-5
Figure 11-13.
815
Pressure
System, Basic with
Deicer and 8-4, 8-5
or
8-7
Autopilot
Installation
11-23
~eechcraft
BARON 55 AND 58
SHOP MANUAL
16 to 19 psi on the deicer pressure gage with the
deicer system ON. A pressure of 17 to 20 psi on the
test gage in the nacelle should be sufficient to obtain
the 16 to 19 psi reading on the deicer pressure gage.
f
the
airplane.
Repeat step
h.
Locate the gyro instrument adjustable orifice (TEthrough TE-767) or the regulator valve (TC-2003
452
on
opposite
side of the
g.
TE-768 and after; TH-I and after)
the LH side of the airplane, forward of the instru-
through TC-2102;
on
ment
adjust
1.
panel,
as
near
the top of the
upholstery panel
and
follows:
Adjust the low-pressure section of the presregulator (section with solenoid) to obtain a readof
ing 7.5 +.5 psi on the deicer pressure gage with the
deicer system OFF and the autopilot ON. A pressure
of 9.0 psi on the test gage in the nacelle should be
sufficient to obtain the reading of 7.5 +.5 psi on the
1.
sure
deicer pressure gage.
Adjust the high-pressure section of the presregulator (section without solenoid) to obtain a
reading of 16 to 19 psi on the deicer pressure gage
with the deicer system ON. A pressure of 17 to 20 psi
2.
sure
on
Loosen the check nut and rotate the orifice
body (adjusting screw on the regulator) to obtain a
reading of 5.0 +.1 -.2 in. Hg on the gyro pressure indicater with both engines operating at 2300 rpm.
the test gage in the nacelle should be sufficient to
reading of 16 to 19 psi on the deicer pres-
obtain the
sure
gage.
Repeat step
c.
the
Tighten
i.
After adjusting the gyro pressure orifice (regulator),
the pressure on the test gage in the turn coordinator
supply line should be rechecked with each engine
operating individually at 2300 rpm. If the pressure on
the test gage has been affected by the adjustment of
the orifice
should be
(regulator),
readjusted
the
as
in the nacelles
regulators
specified in steps c through g.
With both engines operating at 2300 rpm, the difference between the pressures on the test gages at
the pressure regulators in the nacelles should not
j.
exceed .5
psi.
side of the
airplane.
Rotate the pressure regulator adjusting
clockwise to increase pressure
and counterclockwise to decrease pressure.
d´•
452
Locate the gyro instrulment adjustable orifice (TEthrough TE-767) or the regulator valve (TC-2003
through TC-2102,
on
TE-768 and after, TH-1 and after)
airplane forward of the instru-
the LH side of the
ment panel, near
adjust as follows:
1.
body
the
top
upholstery panel
of the
Loosen the check nut and rotate the orifice
to obtain a
reading
of 5.0 +.1 -.2 in.
gyro pressure indicator with both
2300 rpm.
2.
and
Tighten the
Hg on the
engines operating at
check nut and recheck the gyro
are with both
pressure indicator to read in the green
engines operating at 1500 rpm.
requirements of this adjustment
procedure cannot be obtained, the complete system, including the check valves
and the gaskets in the manifold, should
If the
After
adjusting the gyro pressure orifice (regulathe pressure on the gage in the nacelle should be
rechecked with each engine operating individually at
e.
tor),
be checked for leaks and/or restrictions;
then repair any discrepancy and readjust
the system.
Remove the test gages from the
opposite
screws
NOTE
k.
on
NOTE
the check nut and recheck the gyro
indicator
to read in the green are with both
pressure
1500 rpm,
at
engines operating
2.
b
2300 rpm. If the pressure on the test gage has been
affected by the adjustment of the orifice (regulator),
the
regulator in the naceles should
specified in steps b and c.
airplane,
be
readjusted
as
BASIC PRESSURE SYSTEM WITH DEICER AND
I
NOTE
H-14 AUTOPILOT
If the
requirements of this adjustment
procedure cannot be obtained, check
the complete system (including the
check valves and manifold gaskets) for
leaks and/or restrictions, then repair the
discrepancy and readjust the system.
(Flgurell-14)
Install a test gage (0-20 psi) at the "out" side of
each two-stage pressure regulator.
a.
b.
Operate
one
engine
at 2300 rpm and
adjust
two-stage pressure regulator for that engine
lows:
11-24
as
the
folf.
Remove the gages from the
airplane.
515
Beechm~aft
BARON 55 AND 58
SHOP MANUAL
ARROW INDICATES
DIRECTION OF
ALR FLOW
OU?
ADJUSTABLE ORIFICE
RE GU LATOR
VENT LINE
C==--~cJ
-I
r
ii
PRESSURE LINE
OVERBOARD
I I
IIGYRO" LDIRECTIONIY
ILH_O_RI_Z_ON GYRO
GYRO
HORTZ ON
~----,7
TO
DEIC~R
LDIRECTION
GYRO
SYSTEM
AUTOPILOT VALVE
WITH DEICER ON
RESTRICTOR
TO H-14
II
)I
AUTOPILOT
II
L-AUTOPILOT VALVE
PRESSURE
WITH DEICER OFF
INDICATOR
DEICER
GYRO
PRE SSURE
INDICATOR
-t
i
CHECK VALVE’
LMAMFOLD
LCHECK VALVE
TER
TEST GAGE
TWO-STAGE
PRESSURE REGULATOR
ol
i
I
10
PUMP
TER
Figure
E15
11-14. Pressure
System, Basic
-I
with Deicer and H14
1
Autopilot
55-192-6
Installation
11-25
aeechcraft
BARON 55 AND 58
SHOP MANUAL
PNEUMATIC PRESSURE SYSTEM
SURFACE DEICE (TE-452 THROUGH
be
accomplished by inserting
top of the relay
the hole in the
TE-1201, TC-2003 AND AFTER, TH-I
a
screwdriver
and
ing screw in a clockwise direction
turning the adjusting screw in a
The
RESURFACING DEICER BOOTS
pressure-operated surface deicer system consists
lightweight pneumatic deicer boots cement bonded
to the wing and empennage leading edge surfaces,
two engine-driven dry air pumps which provide pressure for boot inflation and evacuation, a pair of air filters to remove contaminates from the
air, and
a
dis-
tributor valve located in the aft section which shuttles
the air flow to and from the deicer boots. In operation
the
engine-driven pumps supply filtered
air
through
the pressure relief valves and the air filters to the
manifold located in the center section beneath the
pilot’s
and
copilot’s floorboards.
Air from the manifold
is directed forward to the instruments
or aft to the distributer valve. The air then passes through the distributer valve to the deice boots for inflation. When the
distributor valve is actuated to inflate the boots, a time
delay relay is actuated at the same time. After 5 to 8
seconds, the relay returns the distributor valve to the
original
position. In the evacuate position,
through an integrated venturi to
create a vacuum in the deicer supply lines to hold the
boots in the down position.
or
evacuate
the air flow is routed
The deicer control switch
on the panel has two posiplacarded AUTOMATIC and MANUAL. Either
position may be selected. In the automatic mode, the
boots will have only one inflation cycle of 5 to 8 secends. The manual cycle will inflate the boots as long
as the switch is held in this position. When the switch
is released the boots will return to the deflated position. The system pressure may be monitored by a
tions
deice pressure gage mounted on the instrument
panel. Regulator adjustments for the two-stage regulater and the distributor and the sequence in which
they should be regulated may be found under the
appropriate pneumatic pressure system heading
found in this section.
TIMER RELAY ADJUSTMENT
The timer
relay that controls the inflation time of the
deicer boots is located under the floorboards of the
passenger compartment just forward of the main spar
the left-hand side. If the deicer boots do not inflate
5 to 8 seconds when the switch is in the AUTOMATIC
position, the timer relay may need adjusting. This can
on
11-26
through
adjust-
the
ing screw until a 5 to 8 second inflation time is established. Inflation time is reduced by turning the adjust-
THROUGH TH-1471 EXCEPT AIRPLANES
EQUIPPED WITH KITS FULFILLING
FLIGHT lN ICING REQUIREMENTS)
of
turning
and increased
by
counterclockwise
direction.
Static electric
charges, if allowed to accumulate,
eventually discharge through the boot to the
metal skin underneath, causing static interference with
radio equipment and possibly puncturing the rubber.
Such static charges are also a temporary fire hazard
after each flight. To dissipate static electric charges, a
thin coating of conductive cement is applied over the
would
neoprene of the boot.
From time to time it may become necessary to restore
conductivity to efficiently dissipate such charges.
The principle factors involved when resurfacing seems
the
advisable
are:
If the
surfacing
material has abraded
Off; if the surfacing has developed cracks; if conductiv-
ity is low.
The
following procedure
resurfacing deicer boots:
a.
should be followed when
Clean the deicer boot
thoroughly
with
a
mild soap
and water solution.
b.
Roughen
sandpaper.
c.
the entire surface of the boot with fine
Clean the entire surface
free cloth moistened with
again
with
a
clean, lint-
mild soap and water solution. Rinse with clean water to remove all traces of the
a
soap.
d.
Apply masking tape beyond the upper and lower
trailing edges, leaving a1/4-inch gap of bare metal.
e´•
B’USh
allow it to
one coat
dry
ating
of A568 cement
at least one
c0at and allow it to
aS
dry
the deicers. The
the cement is
on
the boot and
hour, then apply
a
second
at least four hours before oper-
airplane
may be flown
as soon
dry.
NOTE
If A56B cement has
aged
3 months
or
more, it may be necessary to dilute it
with toluol to obtain the proper brushing
consistency. Mix thoroughly approximately 5 parts cement to one part toluol.
SURFACE DEICER BOOT REPAIRS
Minor scuffed areas
restoring
I
on the boots normally require only
the conductive surface in the immediate
815
I
Qeechc~rt
BARON 55 AND 58
SHOP MANUAL
VERTICAL
STABILIZER
L.H.
I
STABILIZER
R.H.
STABILIZER
VENTURI
DISTRIBUTOR VALVE
TO AUTOPILOT
DEICE
PRESSURE
GAGE
R.H.
I
WING
L.H.
WING
MANIFOLD
TO AIR
PUMP
(PRESSURE)
I
1
I
I
TO Am PUMP
(PRESSURE)
60-603-17A
Figure
11-15. Pressure
System
with Surface Deicer
TH-1
E15
(TE-452 through TE-1201,
through TH-1471)
TC-2003 and after, and
11-27
aeechcraft
BARON 55 AND 58
SHOP MANUAL
however, if the entire surface ply has been
removed, exposing the brown natural rubber underneath, or if the boot is cut, torn or ruptured, it is necarea;
essary to
patch
the
B.F. Goodrich
damage.
Repair
Kit
No. 74-451-C contains cold
suitable for
repairing damaged
area.
on
boot, however, is
temporary
of
repair,
a
patches
cold patch
A
or
nized
repair. Cold patch repairs
following methods:
Clean around the
damaged
b.
Select
factory
for
a
be made
can
a
the buffed
second
soon as
apply one light
extending
area
conductive surface. Allow the
thoroughly (at least one hour) and apply
dry
light
area.
coat. The
the cement is
airplane may be flown as
dry; however, do not operate
the deicers until the cement has dried for at least four
hours.
by
the
SURFACE DEICER BOOT REMOVAL
with
area
or
a
clean lint-
uncontaminated,
a
minimum amount of toluol to the
seam
Apply
line of the
boot while
exerting just enough pressure to peel back
slowly enough for the solvent to underboot to prevent damage to the boot surface.
the boot. Work
gasoline.
cut the
a
half
NOTE
Buff the area around the
damage with steel wool
sandpaper to remove the conductive coating
and thoroughly roughen the exposed surface.
c.
or
beyond
cement to
patched
vulca-
patch which will extend at least one
beyond the damaged area in all directions.
inch
To restore the conductive surface,
coat of A56B cement to the
Soften the adhesion line of the boot with toluol.
free cloth moistened with toluol
nonleaded aviation
deicer
emergency method
opportunity the boot should
and at the first
be removed and returned to the
a.
a
j.
Use as little solvent as
brush or long-spouted oil
fine
possible
on
a
can.
SURFACE DEICER BOOT INSTALLATION
NOTE
locally
manufactured buffing shield will
assure a neater job. The shield can be
fabricated from any thin sheet material
such as acetate, steel, etc., formed into
long strips and taped to the boot around
the perimeter of the damaged area,
Remove the buffing shield after the area
has been buffed.
d.
Wipe
the buffed
area
moistened with toluol
gasoline
or
with
e.
Brush
repair kit)
clean lint-free cloth
uncontaminated, nonleaded
to remove all loose
the
a
particles.
(supplied in
corresponding to the patch.
Remove the backing from the patch and apply one
coat of cement to that surface of the patch.
f.
one even
on
coat of No. 4 cement
the boot
Allow the cement to set until
Clean the
area to be covered by the boot with a
grease-free cloth soaked in methyl ethyl ketone.
Change cloths frequently, and never dip a used cloth
in the clean supply of methyl ethyl ketone.
a.
A
clean
b.
Reclean the metal surface with
surface
Vigorously scrub the metal surface with a clean,
grease-free cloth wetted with Turco Metal-Glo No. 3.
After one minute wipe the surface dry with a clean dry
cloth. Cover the cleaned surface with kraft paper and
wait an hour before rechecking the surface for cleanliness with
picks
the center
h.
patch carefully to avoid trapping
patch thoroughly, starting from
and working to the edges,
mended that persons handling the
cleaner wear rubber gloves even though
the cleaner is harmless to skin if immediately washed off with water.
patch to set for ten to fifteen minutes,
wipe the patch and surrounding area with a clean
lint-free cloth moistened with toluol
or
uncontami-
Satisfactory
adhesion of the
11-28
d.
Carefully
clean the
least twice with
patch
will be reached
in about four hours; however, the boot may be inflated
to check the repair after a minimum of 25 minutes.
CAUTION
Use plastic, not metal, containers for
Turco Metal-Glo No. 3 It is also recom-
Roll the
nated, nonleaded gasoline.
i.
clean, dry white cloth. If the clean cloth
preceding steps.
i
Allow the
then
a
up any dirt, repeat the
tacky.
the remainder of the
pockets.
clean cloth
methyl ethyl ketone, then quickly wipe the
dry with a clean dry cloth.
c.
g. Position the patch over the boot and make contact
with one edge or the center of the patch. Work down
air
a
soaked with
a
rough
backside
on
the boot at
clean, grease-free cloth moistened
with toluol.
Change cloths frequently to avoid reconportions of the boot. If necescontinue wiping the boot until completely clean.
taminating
sary,
the cleaned
515
’iS>eechcraft
BARON 55 AND 58
SHOP MANUAL
NOTE
If the finish of the back of the boot is
For
smooth, mechanically roughen the bond-
EC1403 cement with
ing
2
surface before
Mask off
e.
inch
f.
NOTE
beyond
Open
a
portion
of the metal surface 1/2 to 3/4
dilute the
solvent blend of
No. Ford cup will empty in 20 seconds.
the container and
thoroughly stir the
EC1403 cement with a stick. Do not attempt to use
cement that has jelled too much to drip from the stick,
NOTE
h.
S"ap a chalk line along the center of the leading
edge of the airfoil. Snap a corresponding chalk line
lengthwise along the center line of the cemented side
of the deicer boot.
i.
Attach hoses to the deicer boot connections withleaving fingerprints on the cemented side of the
boots.
out
Do not apply the cement at a relative
humidity higher than 80 percent or under
extremely dusty conditions. The table
below will serve as a further guide for
application of the cement.
In "F
a
parts petroleum naphtha to one part
methyl ethyl ketone (18, 19, Consumable Materials Chart, Section 2) until a
cleaning.
the actual boot area.
Temperature
spraying consistency,
Drying
Time In Minutes
Above 80
j. Using a clean, lint-free cloth heavily moistened
(but not dripping) with toluol, reactive the cement on
the airfoil leading edge and boot in spanwise strips
about 6 inches wide and 24 inches long. Match the
boot chalk line to the leading edge chalk line, and roll
the boot surface spanwise along the leading edge with
a
30
Finch rubber roller to
remove
all air from between
the
60 to 80
45
Below 60
60
g.
Either of the two
to
the cement:
apply
1.
Brush
following
one even coat
methods may be used
of EC1403 cement
on
adjoining surfaces. Rubbing the cemented surfaces excessively will remove some of the cement. If
the boot is misaligned, pull it free quickly with a quick
motion and reposition it properly.
k.
Activate the cemented surfaces and roll
on
each
top half and lower half of the boot in sequence. Exerting pressure, use the 2-inch roller on the entire sur-
both the deicer boot back and metal surfaces. After
face of the boot
permitting the cement to dry for at least 30 minutes,
apply a second even coat to both surfaces.
use
parallel with the inflatable tubes and
the narrow stitcher roller between the tubes. Take
care
to avoid
entrapping
air
throughout
the
rolling
If
an air blister does occur, insert a hypooperation.
dermic needle into the blister so that the air can
escape, then press the surface down until the adhe-
NOTE
Brushing
too
long
in
the cement to "roll"
one area
or
"ball
will
cause
sive surface seals.
up".
~rI
Allow the second coat to
and
preferably
an
dry for at least 30 minutes,
hour, before installing the deicer
CAUTION
boot.
If the blister is within the inflatable tube
2.
I
Using
spray gun (Binks No. 7 with a No. 63
PB head, DeVilbiss JGA 75X, or their equivalent),
spray one even coat of EC1403 cement (60, Consuma
able Materials Chart, Section 2) on both the deicer
boot back and metal surfaces. After permitting the
dry
for at least 30 minutes, spray a second
cross-coat on both surfaces. Allow the second
cement to
even
coat to
dry
for at least 30 minutes, and
hour, before installing the deicer boot.
815
preferably
an
be careful to avoid
area,
puncturing
tubes.
I´•
Clean off all
exposed
edge.
cement up to within 1/4 inch
of the boot
Install
masking tape
around the boot for uniform
m.
edge lines,
then
all
exposed cement and fair
edges and trailing edges of the boot
with EC801 sealing compound.
cover
around all cut
11-29
BARON 55 AND 58
SHOP MANUAL
After the cement and sealing compound have
n.
dried and cured, remove the masking tape and clean
the surface adjacent to the boot with methyl ethyl
ketone. The airplane should not be flown for another
the solenoid in the low pressure tin the nacelle) must
actuate (removing that regulator from the system),
allowing high pressure
air from the second
regulator
into the system.
12 hours.
NOTE
SURFACE DEICE
(TH-1472
AND
Airplanes manufactured
without surface
deicers will not have the instrument
pressure regulator located forward of the
AFTER, AND AIRPLANES
EQUIPPED WITH KITS FULFILLING
FLIGHT-IN-ICING
I(Flgure
REQUIREMENTS)
pilot.
11-16)
The
pressure-operated surface deice system consists
primarily of lightweight pneumatic deice boots bonded
to the wing and empennage leading edge surfaces,
and two engine-driven dry-air pumps which supply air
pressure for boot inflation and evacuation. The surface deice system receives its air from the instrument
air pumps on each engine. The air is drawn in through
the air filter mounted on the engine rear baffle. From
this point on the air passes through the pump, two-
stage regulator, in-line filter, and the check valve into
the manifold (located on the left side of the airplane
under the pilot’s floor). From the manifold the instru-
PRESSURE PUMP REMOVAL
a.
b.
pull
approximately F.S. 207) and is converted to
Hg, of vacuum by the ejector. This vacuum is
used to positively hold the boots down when the deice
system is turned off or during the deflate portion of the
cycle.
Remove pump inlet and outlet hoses from the
Remove the four attaching nuts and washers and
the pump straight aft.
PRESSURE PUMP INSTALLATION
NOTE
When installing a new pump, replace the
in-line filter, and blow out the line
between the filter and the pump. Make
tor, thus dividing into two separate systems at this
plane
to the accessory section of the eng-
access
pressure pump.
c´•
ment air is routed forward to the instrument pressure
regulator while the deice air is routed aft to the ejec-
point. On airplanes equipped with surface deicers the
nacelle regulator is actually an assembly with hnro
regulators. The first regulator sets the pressure at
approximately 5.5 psi. The second regulator, which
does not function except during the boot inflation
cycle, sets the pressure at approximately 18.5 psi.
(Another regulator, located forward of the pilot, further
reduces the air pressure to approximately 5.0 to 6.0
in. Hg. for the instruments.) This 5.5 psi of air pressure
(from the first regulator) operates the ejector (part of
the duplex valve located in the aft fuselage of the air-
Gain
ine compartment.
certain the inlet line to the pump is clean.
If the inlet line to the pump contains for-
eign material, the new pump will ingest
this material, which may destroy the new
pump. Never use an air pump which has
been dropped or mishandled.
a.
Install
a new
gasket
on
the
mounting pad flange.
NOTE
Never jam or force the
engine mounting pad.
pump onto the
at
5.0 in.
When the system is turned on, it may be placed in
either the AUTO (automatic) or MAN (manual) position. If placed in the AUTO position, a timer located in
b.
the
Position the pump on the mounting pad and install
and washers. Torque nuts to 180-
c.
Reinstallthe
d.
Start the
attaching nuts
220 inch-pounds.
plumbing.
engine
mounting flange, and
pressure readings.
and check for
leakage at the
operation and
check for proper
the aft
fuselage (F.S. 207) near the duplex valve will
control the deicer cycling (1 cycle). In the MAN position the boots will inflate or partially inflate as long as
the switch is held in that
position.
For the boots to inflate, the duplex valve must change
positions, allowing air into the boots. At the same time
11-30
DUAL PRESSURE REGULATOR
(RELIEF)
VALVE
REMOVAL
The dual pressure relief valves are accessible through
the access doors, located on the aft top of both
nacelles.
515
BARON 55 AND 58
SHOP MANUAL
Disconnectelectrical connections.
AIR FILTER INSTALLATION
b.
Remove the inlet and outlet hoses from the valve.
(Figure 11-8)
c.
Remove the
a.
valve, and
screws
remove
and washers, which hold the
(RELIEF)
VALVE
Secure the
d.
Position the dual pressure relief valve and
secure
Closethe
and
secure
the relief valve
clamps.
Connectthe electricalwires.
d.
Replace
access
and
manifold)
door and
b.
secure.
c.
Impurities and foreign matter are removed from the air
by two pressure system filters. The intake filter is
located on top of the engine, ahead of the pressure
pump. This filter should be replaced annually or every
300 hours of service time or sooner, depending upon
operating conditions. The filter element must not be
subjected to solvents and must be replaced if this
occurs. Always reinstall the filter cover with the opening facing down. The in-line filters are located between
the pressure regulators and instruments. The frequency of replacing these air filters will depend upon
service conditions; however, they should be checked
approximately every 100 hours of operation and
replaced every 300 hours of operations, or sooner if
conditions warrant. When operating in localities where
a
great amount of dust
inspected
or
sand in the air, the
replaced at more frequent intervals. Under extreme dusty conditions, it
may be necessary to inspect the filters daily. A
clogged filter reduces air flow and slows up the rotor,
causing improper gyro indication due to a loss of gyroscopic inertia.
AIR FILTER REMOVAL
and
Gain
access to the filter
c.
d.
by opening
Remove the nut, washers, and
cover
Remove the spacer and nut which
Remove the filter,
515
LH and RH
Remove the
clamp,
screws, and washers and
the filter.
AIR FILTER INSTALLATION
a.
Position the air filter and
washers, and
b.
secure
with the
clamp,
screws.
Install the inlet and outlet hoses
on
the filter and
with the
clamps.
Replace the access
secure
c.
(IN-LINE)
nacelle and
door
on
the
top aft of the
secure.
PRESSURE REGULATOR ADJUSTMENT
Locate the pressure regulator and in-line filter
installed in the upper nacelle aft of the firewall.
a.
b´•
Install a test gage (0 to 20
regulator and the in-line filter.
c.
psi range) between
Check that the deicer system is off and
engine
to
adjust
the
the
2,000 rpm.
d.
Adjust the low pressure section of the regulator
(section with the solenoid) to give a reading of 5.0
1.0 .0 psi on the deice pressure gage.
e.
Check that the test gage in the nacelle
exceeds 7.0
never
psi.
serials TC-2102 and after,
TE-1133 and after, and TH-935 and
after that do not have surface deicers
will not have the high-pressure regulator
Airplane
the
engine
from the fil-
ter.
ter.
top of the
NOTE
cowling.
b.
the aft
Remove the air filter inlet and outlet hoses from
(INTAKE)
(Figure 11-8)
a.
on
the air filter.
remove
filters should be
(between dual pressure relief valve
accessible through the access
nacelles.
SERVICING THE FILTERS
there is
(IN-LINE)
are
doors, located
c.
the
on
with the washers and nut.
engine cowling.
The air filters
a.
Install the inlet and outlet hoses
cover
AIR FILTER REMOVAL
screws.
b.
with the
with the nut.
Install the spacer and cover. The cover should be
installed with the cover opening facing down.
INSTALLATION
with the washers and
secure
b.
the valve.
DUAL PRESSURE REGULATOR
a.
i"stall the filter and
a.
(INTAKE)
secures
the fil-
the instrument pressure regulator
located forward of the pilot. On these airplanes, adjust the nacelle regulator so
that the instrument gyro pressure gage
will indicate 5
.1 -.2 in Hg. Omit step d
or
through
k.
11-31
Qeechct~R
BARON 55 AND 58
SHOP MANUAL
HORIZONTAL
DIRECTIONAL
GYRO
HORIZONTAL
GYRO
Y
FILTER D
Y
__jl---,
PUMP
-J
4
F’LTER
-I-----’
INSTRUMENT AIR
PRESSURE INDICATOR
PUMP
REGULATOR
SOLENOID
SOLENOID
DUAL PRESSURE
RELIEF VALVE
LOCATION TO "TEE"
IN TEST GAGE
DIRECTIONAL
GYRO
GYRO
CHECK
FILTER
1
CHECK
FILTER
VALVE
VALVE
DUAL PRESSURE
RELIEF VALVE
PNEUMATIC (DEICE)
PRESSURE GAGE
PRESSURE LINE
VENT LINE----
RH WING
LH WING
DEICE DUPLEX
VALVE
EJECTOR
LH STABILIZER
RH STABILIZER
I
55-603-100
VERTICAL STABILIZER
Figure
11-32
11-16. Airfoil Deice
System Schematic
515
a8e6hcraft
BARON 55 AND 58
SHOP MANUAL
Adjust the high pressure section of the regulator
(section without the solenoud) to 16 to 19 psi on the
f.
deice pressure gage.
g. Check that the test gage in the nacelle
exceeds 20 psi.
never
engine
Repeat
engine.
preceeding procedure
b.
opposite
a
reading
of 4.8 to 5.1 in.
Hg.
on
o.
(located
side) to
by
the boot with
cloths
and
never dip a
frequently,
supply of methyl ethyl ketone.
a
used cloth
clean cloth saturated
If the surface to be covered by the boot
and the edge sealer is painted with
epoxy and has a glazed appearance,
remove the gloss with 400-grit sandpaper. (Do not remove the epoxy paint.)
Use a clean cloth wetted with methyl
ethyl ketone to remove the dust.
d.
wait
Check that the test gages in the nacelles
eating within .5 psi of each other with both
are
indi-
engines
running,
Cover the cleaned surface with kraft paper and
one hour before rechecking the surface with a
clean
dry,
white cloth. If the clean cloth
dirt repeat the
picks
up any
cleaning.
Carefully clean the rough backside of the boot at
a clean, grease-free cloth moistened
with methyl ethyl ketone (19, Consumable Materials
Chart, Section 2). Change cloths frequently to avoid
recontaminating the cleaned portion of the boot. If
necessary, continue cleaning the boot until completely
e.
If the test gages do not indicate within ~t .5 psi of
p.
each other, this is an indication of a leak or restriction
which must be located and corrected.
engine
Reinstall the
down and
access
remove
the test gages.
doors.
least twice with
clean.
SURFACE DEICER BOOT REMOVAL
NOTE
Should it become necessary to remove or loosen the
deicer boot, use methyl ethyl ketone (19, Consumable
smooth, mechanically roughen the bond-
Materials Chart, Section
ing
515
a
NOTE
are.
r.
to be covered
the instrument
Set the engine at 800 rpm and check that the
n.
instrument pressure gage still indicates in the green
Shut the
area
methyl ethyl ketone (19, Consumable Materials
Chart, Section 2), then quickly wipe the surface dry
with a clean dry cloth.
tight.
o.
portion of the leading edge surface 1/2
beyond the actual boot area.
a
inch
Reclean the surface with
arc.
q.
an
Clean the
Set the engine at 800 rpm and check that the
instrument pressure gage is indicating in the green
are
allow the solvent to under-
clean, grease-free cloth saturated with methyl ethyl
ketone (19, Consumable Materials Chart, Section 2).
i.
Check that all check nuts
o
and may be reinstalled.
Mask off
pressure gage.
m.
long
with
rpm.
instrument pressure regulator
forward of the instrument panel on the left
obtain
slowly enought
in the clean
Adjust the
a
the solvent.
boot, thus preventing damage to the boot. If
is exercised in removal of the boot, it will not be
Change
Steps j through o may be accomplished
engine running.
k.
apply
with
to remove the boot. The boot should be
to 3/4 of
with either
Adjustthe engineto2,300
can
EQUIPPED WITH KITS FULFILLING
FLIGHT-IN-ICING REQUIREMENTS)
NOTE
j.
squeeze bottle to
applied
a.
the
pump-type oil
SURFACE DEICE BOOT INSTALLATION
(TH- 1472 AND AFTER, AND AIRPLANES
down.
on
plastic
a
minimum amount of solvent while tension is
care
Do not remove the test pressure gage at
this time.
the
brush,
a
damaged
NOTE
i.
or a
a
cut the
When complying with steps f and g, turn
the deice system to AUTO and the gage
should show a pressure rise to 16 to 19
psi, then sink back to approximately 5
psi within 10 to 15 seconds.
Shut the
spout
Apply
removed
NOTE
h.
sion line. Use
2) solvent to
soften the adhe-
If the finish
on
the back of the boot is
surface before
cleaning.
11-33
I
~eechcraR
BARON 55 AND 58
SHOP MANUAL
f.
Open
NOTE
the container and
thoroughly stir the
(60, Consumabler Materials Chart,
Section 2) with a stick. Do not attempt to use cement
that has jelled too much to drip from the stick.
EC-1300L cement
For
spraying consistancy dilute the
EC-1300L cement (60, Consumable
Materials Chart, Section 2) with a solvent blend of 2
parts petrolium naptha to
part methyl ethyl ketone (18, 19,
Consumable Materials Chart, Section 2)
until a No. 4 Ford cup will empty in 20
NOTE
one
Do not
tions
ity
apply the cement if dusty condiprevelant, if the relative humidhigher than 80 percent, or if the
are
is
temperature is lower than 40"F. The
table that follows
the proper
provides a guide
application of cement.
I
seconds.
h.
for
Snap
a
chalk line
line of the airfoil.
along
along the leading edge centerSnap a corresponding chalk line
the centerline of the cemented side of the deicer
boot.
Temperature
Drying
Time in Minutes
Above 80"F
30
60"F to 80"F
45
40"F to 60"F
60
If the boot has a white centerline the
chalk line on the boot is not necessary.
i.
g. Either of these two methods may be used to
the cement.
1.
Brush
one
even
apply
dry
for at least 30 minutes
apply
NOTE
Brushing
to
long
in
one
or
place will
up".
cause
"ball
Allow the second coat to
30 minutes
(preferably
boot.
one
dry for at least
hour) before installing the
NOTE
The brush
application
method is pre-
ferred
2.
Using
(binks No. 7 with No. 63 BP
or equivqalent) spray one
even coat of EC-1300L cement (60, Consumable
Materials Chart, Section 2) on both the deicer boot
and the leading edge surface. After permitting the
cement to dry for at least 30 minutes, spray a second
even
and
a
coat on both surfaces. Allow at least 30 minutes
preferably
11-34
on
airplane
air hose with-
the cemented side of the
NOTE
Applying
a vacuum
to the deicer boot
may aid in installation.
j. Using a clean lint-free cloth heavilly moistened (not
dripping) with toluoil (20, Consumable Materials Chart,
Section 2), reactivate the cement on the airfoil leading
edge and the boot in spanwise strips about 3 or 4
inches wide and 24 inches long. Match the boot centerline with the leading edge chalk line. Roll the boot
surface spanwise along the leading edge with a a-inch
rubber roller to remove all air from between the adjoining surfaces. Rubbing the cemented surfaces excessively will remove some of the cement.
NOTE
If the deicer should attach "off course"
spray gun
head De Vilbiss JGA75X
I
leaving fingerprints
a
second coat to both surfaces.
the cement to "roll"
Attach the deicer boot to the
coat of EC-1300L cement
Materials Chart, Section 2) on both
the deicer boot and the bonding edge surface. After
the cement
out
boot.
(60, Consumable
letting
NOTE
one
hour before
installing
the boot.
(centerline not connecting with each
other), apply methyl ethyl ketone with a
small brush or squirt can to soften the
bond line, apply a minimum of solvent to
the bond line while applying tension to
peel back the deicer boot. Remove
slowly enough to allow the solvent to
softer the cement, thus preventing
removal of the cement coat or damage
815
I
BARON 55 AND 58
SHOP MANUAL
using excess solvent,
twisting the boot, bending the boot
sharply or jerking the boot loose from
to the boot. Avoid
r.
pulled
NOTE
The airplane may be flown 24 hours
after the final installation.
blister is noted on type
25S boots after installation, the boot will
have to be removed as described earlier
If an air
pocket
allow to cure 6 to
After the EC-8001 Class A-112 has cured, clean
s.
the boot and surrounding area with methyl ethyl
ketone (19, Consumable Materials Chart, Section 2).
the bonded area. Allow the cement to
dry before continuing with the applica-
tion. Reapply cement if any has
loose.
masking tape and
longer in cool weather.
Remove the
12 hours or
or
SURFACE DEICER--SURFACE COATINGS
type 23S boots the air
removed
be
by inserting a hypodermay
in this note. On
Age-Master No. 1 (75, Consumable Materials Chart,
Section 2) is an effective protective coating for rubber.
Age-Master No. 1 protects rubber against attacks from
ozone and other airborne contaminents. Apply AgeMaster No. 1 as instructed on the Age-Master No. 1
mic needle into the blister and allowing
the air to escape, then press the area
down allowing the cement to bond. If the
blister is in the inflatable tube area,
insert the needle between the tubes,
being careful not to puncture the tubes.
container.
Activate the cemented surface and roll each top
half and lower half of the boot in sequence. Exerting
pressure, use the &inch roller on the entire surface of
k.
the boot
parallel
to the inflatable tubes, and
the
use
stitcher roller between the tubes. Take care to
entrapping air throughout the rolling process.
narrow
avoid
i.
Using
a
sharp knife, trim
A 75-inch edge
the boots
as
required
for
distance must be mainproper fit.
tubes and the edge of
the
inflatable
tained between
the trim. After the trimming process has been completed, roll the entire surface of the boot. Always start
at the centerline of the boot when initiating the rolling
process. Roll the trailing edge with a stitcher roller.
Using
m.
a
cloth
dampened
with
methyl ethyl
ketone, clean off all exposed cement up to 1/8 inch of
the
NOTE
Do not allow the
to the
edge
ketone to
of the boot as it will
methyl ethyl
weaken the cement.
Apply masking tape to the
from the edge of the boot.
n.
boot 1/8 to 1/4 inch
Apply masking tape to the flight
mately 1/2 inch from the edge of the
o.
I
I
p.
Apply
periodic intervals, Icex provides a smooth,
evens out microscopic irregularities
renewed at
polished
film that
the rubber surfaces; therefor, ice formations have
less chance to cling and are removed faster and
cleaner when the boots are operated. Apply Icex as
on
instructed
on
the container.
SURFACE DEICER BOOT CLEANING
The surfaces of the deicer boots should be checked
for indications of engine oil after servicing and at the
flight. Any oil spots that are found should
a nondetergent soap and water solution. It should also be remembered during servicing of
the airplane that the deicer boots are made of soft,
flexible rubber stock which may be damaged if gasoline hoses are dragged over the surface of the boots
or if ladders and platforms are rested against them.
end of each
surface
approxi-
boot.
minimum of 30 minutes.
EC-8001 Class A-112
apply
9´• Using
Consumable Materials Chart, Section
a
between the
brush
masking tape.
2)
use
(63,
to the area
products are injurious to rubber and their
cleaning agent should be avoided. Limited
of Mineral
harmful in
ened
(47, Consumable Materials
the area between the masking
a
Petroleum
use as a
Bostik 1007-P
Chart, Section 2) to
tape, and allow to dry
515
deicer boots. Icex will not harm the boots and offers
added ozone protection. When properly applied and
be removed with
edge,
run
compound (74, Consumable Materials Chart,
Section 2), a product of B. F. Goodrich Company, is a
silicon-based material specifically compounded to
lower the strength of ice adhesion on the surface of
Icex
Spirits
cleaning
(not dripping)
or
nonleaded
gasoline
is not
the deicers if the cloth is dampwith solvent and a dry cloth is
used to wipe the deicer before the solvent has time to
soak into the rubber.
Wash the deicers with a mild soap and water solution
and rinse with clean water when the airplane is
cleaned. The temperature of the soap solution and
rinse water should not exceed 140"F
(60"D.]
11-35
I
~eechcraft
BARON 55 AND 58
SHOP MANUAL
SURFACE DEICER BOOT REPAIR
the brown natural rubber
B. F. Goodrich Kit 74-451-L contains an adhesive
binder/urethane coating system used to restore
cut, torn
weathered deicers. It will smooth roughened surfaces
and fill small cracks when applied per the instructions
furnished with the kit,
Minor scuff
areas on
the boots
underneath,
or
if the boot is
ruptured, it is nesessary to patch. B. F.
Goodrich Repair Kit No. 75-451-C contains cold
patches for repairing damaged areas. A cold patch on
a
of
or
boot, however, is
repair; therefor,
a
temporary
or
emergency method
at the first
opportunity, the boot
should be removed and returned to the factory for a
vulcanized repair. Cold patch repairs can be made following the instructions with the kit.
normally require only
restoring
the surface in the immediate area. However,
if the entire surface ply has been removed, exposing
TROUBLESHOOTING
(TC-2003
PNEUMATIC PRESSURE SYSTEM
AND AFTER, TE-452AND AFTER, THI1 AND
Indication
AFTER)
Probable Cause
Remarks
INSTRUMENT AIR SYSTEM
1.Zero indication
Pump
instrument gage.
button recessed.
on
out recess
a.
Hole in
plugged
plumbing line, line
plumbing disconnected
or
between manifold and gage.
b. Defective gage,
Defective gym horizon
directional gym.
c.
d. Defective
2.
Pump-out button(s)
extended,
a.
Frequent pump replacement.
regulator
Defective pumps.
b. Filter
3.
or
or
line
a.
Inspect plumbing, replace
b.
Replace gage.
c.
or
Inspect instruments and replace
repair as necessary.
d.
Replace regulator.
Replace pump(s).
plugged between
b.
Replace
filter. Clean lines
pump and manifold.
necessary.
c. Defective dual pressure relief
valve.
c.
Replace
d. Hole in line or line disconnected
between pump and manifold,
d.
Inspect lines, replace
a.
or
Partially restricted pump intake
discharge line.
b. Plugged or partially
inlet or in-line filter.
plugged
as
nesessary.
a.
Replace
b.
Replace filters(s).
lines.
a.
Oil in pump.
a.
Replace hose.
5. Erratic air pressure.
a.
Oil in pump.
a.
Replace.
b.
Engine
b.
Replace.
oil seal defective.
as
valve.
4. No pressure at low rpm.
11-36
or
connect lines as necessary.
515
~echcraft
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING
PNEUMATIC PRESSURE SYSTEM
LIGHTWEIGHT AUTOMATIC SURFACE DEICER (PUMP-DRIVEN)
(TC-2003 AND AFTER, TE-452 AND AFTER, TH-1 AND AFTER)
The
following troubleshooting procedures
are
based
pumps
indication
the assumption
operational.
on
are
that the
airplane engine-driven dry
Probable Cause
1. Deicer boots do not inflate
(either
a.
Open
air
Remarks
circuit breaker,
a.
both engines operating at
minimum cruise rpm for a period of
or
Push deicer circuit breaker to
reset.
eight seconds).
b. Loose electrical connections
broken wire.
c.
Time
delay relay
not
or
functioning.
d. Deicer boot puncture.
e.
b.
Tighten
c.
Replace
or
repair
the
as
required.
relay.
d. Repair as prescribed in this
section or replace.
Distributor valves not
e.
See items 4 and 5.
functioning.
f. Piping lines kinked, blocked
not connected.
or
g. Leak in system
2. Deicer boots inflate too
(either
slowly
both engines operating at
minimum cruise rpm for a period of
eight seconds.
or
a.
Piping
blocked,
g. See System Checkout, locate
and repair.
lines kinked, partially
not connected securly.
or
b. Leak in system.
c.
f. Inspect lines and connections;
-blow out lines.
Inspect lines and connections;
blow out lines.
a.
b. See system checkout, locate
and repair.
Deicer boot puncture.
c.
Repair
section
d. Distributor valve not
3. Deicer boots deflate too
slowly.
a.
Clogged
b.
Piping
functioning,
instrument air filter.
or
prescribed
replace.
as
in this
d. See items 4 and 5.
a.
Replace
b.
Inspect
and blow out lines.
c. Overboard line from distributor
valve partially blocked.
c.
Inspect
and blow out lines.
d. Distributor valve not
d. Overhaul
lines kinked
or
partially
air filter.
blocked.
operating
or
replace.
properly.
e.
515
Electrical circuit
malfunctioning.
e.
See system wiring diagram.
1157
~eechcraft
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING
PNEUMATIC PRESSURE SYSTEM
LIGHTWEIGHT AUTOMATIC SURFACE DEICER (PUMP-DRIVEN)
~C-2003 AND AFTER, TE´•452 AND AFTER, TH-1 AND AFTER) (CONT’D)
The
following
items
might
aid in
ascertaining
whether
Indication
4. One or more boots do not inflate
with pressure gage at normal
reading and
timer
or
not the distributor valve is
Probable Cause
Remarks
Defective wiring in external
circuit or other units.
Refer to airplane system wiring
and make check.
Disconnect plug at distributor
valve.
a.
a.
diagram
cycling.
b.Faulty
solenoid in distributor
b. Measure resistance of
solenoids. Reading should be 17.5
ohms
5% through the receptacle
pins. Replace distributor valve if
readings do not check.
valve.
c. Mechanical failure, distributor
valve.
5. One
or more
boots inflate but do
not deflate
gage at
readily with pressure
normal reading timer
functioning properly.
a.
Disconnect the lines at the
outlet ports of the dictributor valve
and check valve operation with a
gage. If thouble is not found in the
distributor valve, inspect boots
and lines for leaks or blockage.
c.
Exhaust port of distributor valve
a.
Route exhaust line to low
not vented to low pressure area.
pressure
b. Vacuum ejector on distributor
valve plugged or partially blocked.
b. Overhaul
valve.
area.
cycling.
c.
Defective boots.
c.
Repair
section
I
located
lation is
a.
old
as
is located
as
e.
a
on
only and is
Strip instal-
follows:
tic 1008
11-38
(48,
strip
to the deicer boot
the "A"
Apply
a
parts (by weight) of the base material
package) with 1 part (by weight) of the
30
tin
the "B"
package).
coat to both the stall
which it will be bonded. Allow to
Clean the boot surface thoroughly, removing all
glue. Mask off the area where the new strip is to
Install the stall
manner:
accelerator
c.
With line disconnected see if
exhaust port is discharging; if not,
replace distributor valve.
cement. Mix the Bostic 1008 in the follow-
two-part
ing
tin
be installed and wipe with methyl ethyl ketone
Consumable Materials Chart, Section 2).
b.
in this
e. Mechanical failure in distributor
valve.
the left wing
indicated in Figure 11-17. Stall
accomplished
prescribed
replace.
as
or
d. Disconnect line from exhaust
port of distributor valve and see if
line is clear to low pressure area.
(Figure 11-17)
strip
replace distributor
d. Obstruction of lines.
STALL STRIP INSTALLATION
The stall
or
using
(19,
Bos-
Consumable Materials Chart, Section
2),
then install the
strip
as
strip and the area to
dry 10 to 15 minutes,
described in the illustration.
The cement will set in about 6 hours.
d. When dry, coat the
Sealing Chart, Section 2)
area
to
with A56B cement
replace the conductivity
(1,
of
the boot.
E15
~-)eechcraft
BARON 55 AND 58
SHOP MANUAL
IjA
VIEW
A
ROTATED 900
55-600-20
Serial No.
8
m
Wing
TC-I thru TC-1402
111.38
except TC-350
B=14.75 in.
Station Station
to
120.38
B=14.25 in.
Reservoir system
TC-502 thru TC-2002
111.38
Vacuum system
B=14.88 in.
TC-350
123.25
TE-1 thru TE-451
B=14.38 in.
to
120.38
B=14.38 in.
to
132.25
B=14.03 in.
Vacuum system
TC-2003 and after
123.25
TE-452 and after
B=14.38 in.
to
132.25
B=14.03 in.
TH-I and after
Pressure system
TC-1 thru TC-1607
111.38
O
TE-1 thru TE-942
B=14.75 in.
m
except TE-938
E3
TC-1608 and after
TE-938, TE-943
123.25
and after
B=14.28 in.
120.38
B=14.25 in.
to
B=14.78 in.
a
0
111.38
to
120.38
B=14.28 in.
to
132.25
B=13.93 in.
TH-1 and after,
Figure
E15
11-17. Stall
Strip In~tallation
I
11-39
aeechcraft
BARON 55 AND 58
SHOP MANUAL
STALL WARNING SYSTEM ADJUSTMENT
The stall
warning switch
airplane
readjusting, proceed
is
carefully adjusted
factory. Should
when the
is test flown at the
installation
it
require
follows: Locate the switch
the undersurface of the left
on
loosen the two
side of the
as
phillips-head
wing
screws, one on
and
either
vane
NOTE
On
airplane serials TH-1377
and after
the stall
warning switch is adjusted by
loosening the four mounting screws tone
on each corner of the mounting plate).
Tighten the screws after each adjust-
high heat stall warning switch
draws electrical power from its own 7.5-amp circuit
breaker, which is located in the left subpanel. On the
If the stall
vane
coming
Moving
warning has been coming on too early, pull
back and down. If the stall warning has been
on
the
too
late, push the
vane
with the
vane
Phillips
up and forward.
loosened
screw
the entire unit up or down inside the wing causthe switch to be closed earlier or later. Retighten
moves
ing
the
screws
after
making
each
adjustment.
on TH-1377 and after) has an additional
heating element in the mounting plate. The earliest
airplanes (prior to TE-738, to TH-182 and to TC-1936
except TC-1913) were produced with heaters as
optional equipment. Except for installations with high
heat,the stall warning switch draws its electrical power
from the pitot heat circuit breaker. On those installations equipped with a right and left pitot heat circuit
breaker, the stall warning switch heater draws its
power from the left pitot heat circuit breaker.
The heater for the
ment.
the
installation
ground the heater is restricted to operation at 1/4 bus
voltage to prevent overheating. When the airplane
leaves the ground, the contacts in the landing gear
safety switch close to actuate the landing gear safety
relay. Refer to Figure 11-19. When the relay contacts
close, full bus voltage is applied to the stall warning
switch heater. The major components of the system
are as
follows:
NEVER
TRY TO ADJUST THE SWITCH BY BENDING THE
a.
The
7.5-amp circuit breaker
in the left
subpanel.
VANE.
As
rule of thumb, moving the vane 1/4 inch will
change the time the stall warning actuates by about 5
a
mph
of indicated air
speed. The only way to test the
setting is to fly the airplane into a stall,
the
noting
speed at which the warning horn and light
comes on and the speed at which the full stall occurs.
ADJUST UP TO
ACTUATE SOONER
accuracy of the
The stall should be made with the flaps and gear up
and power off. Prior to the stall decelerate no faster
i
than
one mph per second. It may be mecessary to
make several alternate adjustments and test flights
before the desired setting can be reached. The stall
warning should actuate, ideally, at 7 to 9 mph ahead
of the complete stall, although 5 to 10 mph ahead of
the complete stall will meet FAA requirements. The
switch
setting
should be checked and
necessary whenever
adjusted as
wing leading edge is
wing or
extensively repaired or
installed. The switch should require
replaced
a
or
if
a new
no
O
ADJUSTMENTO
O
SCREWS’
i
O
switch is
adjustment
O
3
in
O
normal service.
ADJUST DOWN TO
ACTUATE LATER
STALL WARNING SWITCH HEATER
The stall
ice from
ing
warning switch
forming around
erroneous
have
a
11-40
heater is installed to prevent
or on the switch vane caus-
indications. All of the heated switches
heating element in the switch while the high
(installed as part of optional deice boot
heat switch
60-251-11
Figure
11-18. Stall Vane
Adjustment (TH-1
TH-1377)
thru
515
I
aeechcraft
BARON 55 AND 58
SHOP MANUAL
The 16-ohm 50-watt resistor attached to the
b.
inboard side of the rib at
wing
station 45.0.
The landing gear safety switch relay located forc.
ward of the main spar carry-through.
d.
The
The
e.
The
landing gearsafetyswitch.
HEAT TEST FOR HIGH HEAT STALL
(OPTIONAL
TH- 1377 AND AFTER)
WARNING SWITCH,
equivalent)
a.
is
an
accurate ohmmeter
8100A
or
The windshield anti-icer may be operated either
Remove the switch from the left
wing.
purple
Disconnect the red
airplane wiring,
c.
Connect the ohmmeter to the red
purple
or
white and
or
wires from
white and
wires.
The ohmmeter should indicate 4.8 to 6.7 ohms.
If the indication is correct,
reinstall the switch.
e.
I
(Fluke
b.
f.
ON
required.
the
d.
propeller anti-icing system is controlled by a ciron the left subpanel. The amount
of anti-icing fluid available in the supply tank is indicated by a gage on the upper right corner of the
instrument panel. The propeller anti-icing system must
be turned on to supply power to the anti-icing pump
before the windshield anti-icing system can be used.
The windshield anti-icing system is controlled by a
three-position switch mounted on the left subpanel.
cuit breaker switch
5-amp stall warning circuit breaker.
For this test
lage, where it connects to the discharge tube that runs
along the lower edge of the pilot’s windshield. The
discharge tube has five orifices equally spaced for
effective diffusion of the anti-icing fluid.
If the indication is incorrect,
remove
the wires and
the switch.
ANTI-ICING SYSTEMS
Since the orifices in the
discharge tube are small
propeller and
.0210 inch in diameter for the windshield) and easily
plugged, the system should be periodically checked to
~.0130/.0225 inch
ensure
(Figure 11-23)
in diameter for the
that proper fluid flow is maintained. The proshould be checked to ensure
peller anti-icing system
PROPELLER AND WINDSHIELD
ANTI-ICING MAINTENANCE
isopropyl alcohol used by the propeller and windshield anti-icing system is supplied by a three-gallon
The
tank located beneath the floor
p’ecautions:
a.
replace
con-
tinuousiy (when the switch is in the ON position) or
momentairly (while the switch is held in the MOM. ON
position). When the control switch is actuated, power
is supplied to open the solenoid valve that regulates
the flow of anti-icing fluid to the discharge tube at the
pilot’s windshield. To ensure proper operation of the
anti-icing system, observe the following maintenance
on
the left side of the
that 2.25 to 2.75 quarts per hour per
propeller
is main-
tained.
b.
To prevent the orifices in the
becoming clogged
screen
or
discharge
tubes from
restricted, periodically clean the
located at the bottom of the anti-icing pump
only with clean isopropyl alcohol.
and service the tank
baggage compartment. The filler cap to the tank
through a door in the nose compartment
floor. The supply line from the tank is routed directly
aft to the pump that provides the pressure to operate
the anti-icing system. The outflow line from the pump
is routed aft under the floor and outboard along the
wing leading edge to the right side of each nacelle,
then forward to the slinger rings on each propeller.
The flow of anti-icing fluid to the propeller is controlled
by two orifices located at the ends of the discharge
tubes at the propeller slinger rings. On airplanes
equipped with the optional windshield anti-icing system, another line from the anti-icing pump tees off to
the solenoid valve that regulates the flow of anti-icing
fluid to the windshield anti-icing discharge tube. This
valve is mounted just outboard of the pump and the
on
the upper LH side of the forward closure.
c.
line from the valve is routed to the center of the fuse-
aft
Locate the potentiometer adjustment screw on the
printed circuit board in the junction box. Turn the
nose
is accessible
515
c.
Drain and flush the
supply
tank twice
a
year.
Check the clearance of the discharge tube to the
anti-icer boot with the propeller blade rotated to the
low pitch stop. Adjust the discharge tube centerline to
d.
discharge
the
anti-icing
fluid onto the anti-icer boot at
the foreward groove of the boot with the tube
th, boot by .06
.03 inch.
clearing
ANTI-ICE FLUID INDICATOR
GALIBRATION
a.
Fill the alcohol anti-ice tank with clean
isopropyl
alcohol.
b´•
Remove the
cover
from the
junction
box mounted
11-41
Ci~eechcraft
BARON 55 AND 58
SHOP MANUAL
either clockwise
screw
anti-ice fluid indicator
d.
Replacethe
counterclockwise until the
or
gives
coveron
a
full
reading.
A maximum temperature of 150"F shall not
be exceeded.
seasons.
INSTALLING THE PROPELLER ANTI-ICE
4.
2)
Locate the anti-icer boot in the
Sight along
1.
edge
and make
a
following
manner:
the centerline of the blade
temporary mark
on
the hub
leading
directly
above this centerline. The mark should be used
guide
in
blade
locating
as a
the boot.
Place the boot
2.
along
the
a)
propeller
Locate the end of the boot
hub
clamp,
one
over
5.
Mask around the
114 inch border
Prepare
the blade for
degree
by
bonding by:
methyl ethyl ketone (19, Consumable Materials
Chart, Section 2).
I
I
the
with
stripping
off the
organic coating,
clean
cloth wet with toluol
(20, Consumable
Materials Chart, Section 2), scrubbing well, and follow
with a clean dry cloth. Finally, clean with a cloth wet
area
a
(not dripping) with methyl ethyl ketone (19, consumable Materials Chart, Section 2) and immediately follow with a clean dry cloth before the solvent evaporates.
c.
6.
Prepare
1.
Mask the
bonding by:
perimeter
edges, after the
2.
I
cement is
applied.
Sand the smooth sides
thoroughly with No.
adhesive
and
clean
with naphtha (18,
280-grit
paper
Consumable Materials Chart, Section 2). The boot is
now ready to install on the blade.
Warm the cleaned blade to 70"F (minimum)
with heat lamps or equivalent heaters and maintain
3.
11-42
a
heavy
coat of Bostic 1008 cement
Materials Chart, Section 2) on the
7.
Allowthesecond
cementcoattodry about30
position. Do this
end center with the propeller
minutes before
placing
by aligning the
inboard
hub mark and
working outward. It is necessary to
lenghtwise over the blade in the area
stretch the boot
the boot into
between the root end and the flat cross section in
order to prevent wrinkling of the boot at the edges.
The outward section of the boot will lay into position
without
glue
stretching
and should fall within 1/4 inch of the
line. Roll the boot
the full
length
firmly by working outward from
of the centerline in order to prevent
u"de’ the boot.
8.
Remove the
the 1/4 inch of
turbed.
glue
masking tape carefully
so
that
around the boot remain undis-
Remove any trapped air with the aid of
hypodermic needle and roller.
10.
the ribbed side with
on
1/4-inch tape to prevent excessive curling of the feathered
Brush
9.
the boot for
is
the boot,
with
After
cure
on
Remove the paint or other organic coating
within the masked area with a suitable paint stripper.
In many instances, stripping may be accomplished
2.
of tackiness is indicated, additional
applying the bonding cement.
needed before
the boot. Allow to stand 45 minutes and repeat the
brush coat operation on both the surfaces.
1.
I
thin coat of Bostic 1007P cement
(48, Consumable
amount of stretch.
b.
a
the lead-
all sides except for the
outer end where the border is increased by the
a
Brush
blade.
covered
area
on
I
primer ~47, Consumable Materials Chart, Section 2)
over the entire cleaned area of the blade and let dry
inch from the
the boot, locate the centerline of the boot
propeller
of the blade. Allow one
Chromalox heaters at 150"F. Check the perimeter for
hardness by scratching with a thumb nail. If any
then locate the centerline of the
centerline of the
area
dry.
for up to three hours. This time may be shortened to
30 minutes by accelerated aging under heat lamps or
boot 1/8 to 114 inch forward of the leading edge cenon the propeller blade. At the outboard end of
ing edge
the entire cleaned
hour to air
terline
leaving
apply one thin uniform coat of EC776
(46, Consummable Materials Chart, Section
of the
leading edge
follows:
as
3.
Brush
cement
BOOT
a.
temperature throughout the installation.
heating operation is-unnecessary during warm
The
box.
thejunction
this minimum
Allow the installation to
turbed before
placing
WINDSHIELD
cure
a
48 hours undis-
into service.
ANTI-ICING SYSTEM
(ELECTRICAL) TE- 1169 AND
TH-1080 AND AFTER)
On these
ing
on
airplanes
ice may be
the windshield
by
an
prevented from formelectrical windshield
heater
515
I
aeechcr~ft
BARON 55 AND 58
SHOP MANUAL
sA
STALL WARNING
VANE
PLATE
STALL WARNING SWITCH
8
GEAR SAFETY SWITCH
TO LANDING GEAR
POSITION LIGHT
C.B (5A)
10
16 n sow
7.5A 3,
LANDING GEAR SAFETY
SWITCH RELAY
STALL WARNING HEAT
55-600-19
Figure
515
11-19. Stall
Warning Electrical Schematic
11-43
BARON 55 AND 58
SHOP MANUAL
The windshield heater is of the heated segment
design. The windshield heater is approximately 9.6 X
11.5 inches, conforming to the contour of the windshield and located on the centerline of the airplane.
The windshield heater is controlled by a 20-ampere
toggle-type circuit breaker switch, placarded WSHLD,
located on the left subpanel. With the switch on, 28
vdc of power is applied to the windshield temperature
controller, windshield heater relay and windshield
heater. The temperature controller senses the temperature of the windshield heater. The temperature
controller removes power from the system (deenergizing the relay) when the temperature of the
windshield is between 100"F and 110"F. When the
windshield heater has cooled to a temperature of 90"
to 100"F, power is applied to the system (energizing
the relay) allowing the temperature to rise again. Thus
the temperature controller maintains the temperature
of the windshield heater between
a
temperature of
90"
and 110"F.
T~
CAUTION
Working in the nose baggage compartment, tag
and disconnect the windshield heater wiring from the
windshield heater control box.
a.
b.
Remove the two
Lift up the wire cover. Using a sharp-edged tool,
cut the sealant out of the inside of the wire
cover. Be careful not to damage the wires.
pry
or
e.
Separate
f.
the wires from the wire
cover.
Full the wires up and out of the hole in the fuse-
lage.
Remove the sealant from the hole in the bottom
9.
retainer where the wires pass through to the heater
plate. Be careful not to damage the wires. Refer to
Figure 11-20.
I
NOTE
If it is desired to retain the existing windshield heater plate for continued use,
putty knife-like scraper
a
out of
wood. Sharpen one edge
this tool instead of the putty
or
and use
knife used in step i. This tool will help
prevent scratching the heater plate.
CAUTION
The magnetic compass is erratic when
the windshield heater is in operation. If
the directional gyro is to be reset, turn off
the windshield heat for 15 seconds to
allow a stable reading of the standby
Applying masking tape to the heater
plate will further protect the surface from
scratches.
h.
Using a sharp-edged putty knife or similar tool,
scrape off the sealant around the perimeter of the windhield heater plate. Refer to Figure 11-20.
compass.
NOTE
1
i.
It may be necessary to insert a sharp-edged tool
between the heater plate and the retainers in order to
completely loosen the bond of the sealant. If this is
done, be careful not to pry on the side or bottom
Heat should be applied to the windshield
before ice forms,
retainers,
WINDSHIELD HEATER REMOVAL
TH- 1080 AND
Refer to
j.
an area on
the wind-
approximately 14-inches long by 12-inches
wide above the heater frame. On each side of the
heater frame, apply masking tape along each edge
the entire
out
from the
the
height of the frame and at least 6 inches
edge. This will help to prevent scratching
windshield when removing the windshield heater.
they
as
to break the
shield
11-44
cover.
d´•
Plexiglas
mask off
the wire
by prying it loose. Be careful not to scratch the airplane finish, bend the wire cover or damage the wiring. Refer to Figure 11-20.
1
make
Using masking tape,
securing
tool such
a
or
Ground operation of the windshield
heater is limited to 10 minutes,
(TE- 1188 AND AFTER,
An%R)
screws
Using sharp-edged
as a putty knife or
pocket knife, insert the tool under the edge of the wire
cOve’. loosen the bond of the sealant either by
cutting
C.
are
likely
top retainer,
Figure
to break. It is
as
permissible
replaced.
it should be
11-20.
Start
1
working
top left corner of the windassembly; use a sharp putty knife to
remove the top windshield heater plate retainer. Insert
the edge of the putty knife between the windshield and
the top retainer. Insertion depth should not exceed 1/8
inch. Refer to Figure 11-21. Working along the entire I
length of the top retainer, pry off the retainer and disat the
shield heater
card it. Take
care
not to scratch the windshield.
615
~eechcraft
BARON 55 AND 58
SHOP MANUAL
WINDSH/EL~ HEATER /NSTALLATION
(TE-1169 ANDAFTER, TH-1080 AND
f~l
CAUTION
If the
putty knife is inserted
AFTER
too far
Carefully scuff sand any bonding material and sealant
top attachment strip of the windshield heater
between the windshield and the windshield heater retainer, damage may
occur that could require replacement of
the windshield.
off the
frame.
a.
Make
sure
all sealant is
scraped off
of the heater
retainers.
k. After removal of the top retainer, insert a sharp
tool between the top of the windshield heater plate
and the attachment strip of the windshield heater
frame which is bonded to the windshield. This is nec-
I
essary in order to break the bond between these two
parts. Refer to Figure 11-21 DetailA. Be careful not to
scratch the windshield.
i.
Slide the heater
the
take
existing
care
plate up and out of the frame. if
plate is going to be used again,
scratch it during removal,
heater
not to
b. Clean the windshield and frame with naphtha (18,
Consumable Materials Chart, Section 2) and wipe dry
with
c.
a
heater
d.
clean white cloth.
Cut
piece
plate and
a
of
masking
paper to the width of the
longer than the plate.
2 or 3 inches
Slide the paper down into the heater frame and
tape down the edge. This will help prevent the heater
plate from being scratched during installation.
Slide the new windshield heater plate into the
e.
frame. Ensure that the wires are at the bottom. Guide
TRIP
RETAINERS
I
HEATER PLATE
WIRE COVER~
I
WINDSHIELD
58-110-28
Figure
815
11-20, Windshield heater
11-45
I
~Seechcraft
BARON 55 AND 58
SHOP MANUAL
the wires
Carefully
f.
Lay
through
remove
the
the hole in the bottom retainer.
the
masking paper,
top retainer
onto the heater
plate
position. Trim the ends of the
retainer to obtain a good fit. Apply Mylar tape (62,
Consumable materials Chart, Section 2) to the windshield parallel to, and lightly touching, the upper vertical surface of the retainer. This will prevent getting
adhesive on portions of the windshield where it is
unwanted. Mylar tape is used because the adhesive
new
frame in the installed
I
If sealant does not squeeze out from underneath
o.
the wire cover, apply a bead of sealant around the
bottom edge of the wire cover. Wipe off the excess
sealant.
Remove the tape securing the top retainer.
P´•
Remove the Mylar tape. Apply sealant around the
heater contacts the retainers.
bottom two
moisture
will not stick to it,
Apply
Be
corners.
penetration
sealant to
sure that any possible paths of
have been sealed. Allow the
cure.
Remove the
and connect the
electrical wiring
tags
.q.
x
o
b
temperature
CAUTION
to the windshield heater
Use adhesive and sealant
avoid
spairingly
Turn the power and WSHLD switch on, and place
on the windshield heater to make sure that the
heater is operative.
runs,
Brush on PS-30 adhesive (44, Consumable Mateg.
rials Chart, Section 2) per the instructions on the pack-
If the windshield heater is found to be
s.
ield
directly
CHECK
h.
Apply
strip.
Place the
new
heater retainer in the proper posiplace with masking tape
tion. Secure the retainer in
and allow at least four hours for the adhesive to
Insert the
j.
tip
cure.
of the sealant
applicator into the hole
plate pass through
bottom retainer. Squeeze enough RTV-732 seal(45, Consumable Materials Chart, Section 2) into
where the wires from the heater
the
tna.edisngeti
the hole to
ensure
that
no
operative,
turn WSHLD switch and power off. If the windshield
heater is found to be inoperative, troubleshoot the system
adhesive to the bottom surface of the new
top windshield heater retainer. Apply adhesive to the
portion of the top retainer that butts up against the
ends of the side retainers.
I
hand
age. Apply adhesive to the top horizontal and vertical
surfaces of the top attachment strip of the windshield
heater frame and to the exposed portion of the winds-
i.
control
r.
to
a
above the attachment
sealant to the top
two corners of the windshield heater frame and to the
per the WINDSHIELD HEATER TROUBLESHOOTING CHART and WINDSHIELD DEICER
t.
(electrical)
to isolate and correct the
problem.
Remove all tape from the windshield.
WINDSHIELD HEATER TEMPERATURE
CONTROLLER REMOVAL (TE- 1169 AND
AFTER, TH-1080 AND AFTER)
The windshield
nose
a.
temperature controller is located in the
baggage compartment just
Gain
access
to the controller
baggage compartment
b.
Tag
and
forward of FS 39.00.
remove
through
the
nose
door and locate the controller.
the electrical
wiring
from the
con-
troller.
water can
k.
Remove the clip nuts, washers and screws which
c.
attach the controller to the mounting bracket and
remove the controller.
i.
WINDSHIELD HEATER TEMPERATURE
CONTROLLER INSTALLATION (TE- 1169
AND AF~ER, TH-1080 AND AFTER)
Lay the wire cover in its installed position on the
fuselage. Mark the fuselage along the outer edges of
the wires cover to show where the wires will lay in the
installed position.
Remove the wire cover and apply sealant to the
between the pencil marks.
area
m.
Apply sealant to the inside of the wire
approximately three-fourths full of sealant.
cover
until
Lay the wires down into the sealant that was
applied to the fuselage. Insert the wires down into the
hole in the fuselage and install the wire cover with the
n.
two screws.
11-46
a.
Position the controller
and
secure
b.
Removethetags
on
the
mounting
clip
with the screws, washers and
bracket
nuts.
and connectthe electrical
wiring
tO the controller.
c.
Close and
secure
the
nose
baggage compartment
door.
615
Qeechcraft
BARON 55 AND 58
SHOP MANUAL
WINDSHIELD HEATER RELAY REMOVAL
(TE- 1169 AND AFTER,
AFTER)
The windshield heater
baggage compartment
a.
Gain
access
TH- 1080 AND
is located in the
forward of FS 39.00
to the
nose
adjacent
baggage compartment
nose
door and
temperature controller.
relay through
the
baggage
(ELECTRICAL)
The control box, relay, and heater assembly should all
be checked before any item is replaced.
compartment door and locate the windshield heater
relay,
a.
Tag
relay.
b´•
b.
Close the
WINDSHIELD DEICER CHECK
relay
to the windshield heater
c.
secure.
and remove the electrical
wiring from the
Disconnect the heater from the control box and
relay.
Check that there is
a
circuit
through
the two blue
wires of the heater.
Remove the screws, nuts and washers that hold
the relay in place and remove the relay.
c.
C´•
Check that there is
white
(black and
red
b.
Remove the
relay
in the proper
with screws, washers and nuts.
position
units)
leads of the heater.
If both of these circuits conduct electricis probably functioning
INSTALLATION (TE- 1169 AND AI-TER,
TH- 1080 AND AFTER)
Place the
circuit between the black and
later
NOTE
WINDSHIELD HEATER RELAY
a.
a
on
ity, the heater
properly. If an
tags from the electrical wiring and
wiring to the relay.
connect the electrical
UPPER WINDSHIELD HEATER RETAINER
accurate ohmmeter is
available, a more complete check of the
system may be made as follows:
and secure
1.
Check the
red and
white)
for
heating
a
circuit
(black
and white
or
resistance of 1.69~ 25 ohms.
INSERT PUTTY KNIFE
HERE TO A DEPTH OF
1!8" OR LESS
INSERT PUTTY
KNIFE HERE
WINDSHIELD
HEATER PLATE~
Db
NOT REMOVE
THIS WINDSHIELD HEATER
FRAME A~TACHMENT STRIP
WINDSHIELD
WIN6SHIELD
HEATER PLATE
ATTP;CHMENT STRIP
WINDSHIELD
DETAIL
A
58-110-27
Figure
515
11-21. Windshield Heater Retainer Removal
11-47
BARON 55 AND 58
SHOP MANUAL
The
2.
element in the heater is temperasensitive; therefor, the resistance will vary with
ture
sensing
temperature change. Check the temperature
I
tance chart for the correct
reading.
Refer to
resis-
Figure
the inboard halves of
cycle every
deflect
is
as
theater) cools,
the
a.
Check that the controller turns the heater
the
sense
(88"F
to
element resistance
drops
on as
to 328~ 3 ohms
100"F).
NOTE
As the sense element theater) heats, the
resistance will become greater.
b.
more
the system
Brush replacement is normally required after 500
hours of service. The copper-plated area of each
brush indicates its wear limitations. To prevent the
copper from
be replaced
damaging
110"F).
(GOODYEAR)
(Figure 11124)
The
propeller deicer uses two heating elements per
blade. The timer applies current to the outboard element first and then to the inboard element. The cycling
sequence of the timer starts from the outboard halves
engine prop, then
completes the timer cycle with the outboard halves to
should be
the
as soon as
has been
11-48
cycles, indicating
ELECTRIC PROPELLER DNCER BRUSH
REPLACEMENT (GOODYEAR)
(100"F
to the inboard halves on the left
complete
The system must not be operthan two minutes on the ground as a
visible. Prior to
ELECTRIC PROPELLER DEICING,
I
each element
Checkthatthe controllerturnsthe heater off when
the sense element resistance reaches 338+ 4 ohms
to
a
two minutes. The ammeter hand will
precaution against overheating of the iceguard. After a
8-minute cooling period, the system has cooled sufficiently to permit the second operation. The timer
needs no periodic maintenance. In the event of failure
return the timer to the installing facility.
NOTE
As the sense element
resistance will drop.
prop. Each ele-
operating properly.
ated for
FUNCTIONAL CHECK OF THE
WINDSHIELD HEATER CONTROLS
the?ight engine
ment is heated for 30 seconds to make
installing
slip ring,
the brushes must
the copper
new
plating becomes
brushes, the slip ring
wiped clean with a paper towel or
dampened with-an Acetone-based
rag that
solvent.
Allow to air
dry completely before installing new
brushes. Maintain sufficient clearance between the
brush block and
slip ring by adjusting
the
floating
lock-
nuts in the brush block bracket until the brushes
extend from .08 to .09 inch from the block. Brushes
should be
aligned
to move
freely
in the brush holder
with the entire face of each brush
making contact with
the slip ring throughout 360 degrees of rotation. This
provides preventive measures against arcing, slip ring
pitting, and excessive brush wear.
815
I
~-)eechcraft
BARON 55 AND 58
SHOP MANUAL
MAXIMUM
MINIMUM
0 31
-20~
0´
20´
40´
60´
800
100o
120´
1400
1600
180´
DEGREES FAHRENHEIT
Figure
E15
11-22.
Temperature/Resistance
Chart
11-49
QeechcraR
BARON 55 AND 58
SHOP MANUAL
~1
I
.I´•-
\I
Alcohol
Quantity
Indicator
-r
r
Windshield
Pump
Quantity
Anti-ice Tank
Sensor
7
Anti-ice Slinger Ring
E55-l4Gg
Figure 11-23. Propeller Anti-icer System
11-50
515
aeechcraft
BARON 55 AND 58
SHOP MANUAL
t:::::
j
i
i
PROP. DEICER
CIRC BREAKER
AR~IHT;-IFCIEREWALL
-t
I
PLZiC
PROP. DEICER
7\AMMETER
i~
;j
FIREWALL:
I
ANTI-ICE
PLUG
i
__j
i
LIRUSH BLOCK
c=r_
LDEICER BOOT
DEICER BOOT
55-193-37
Figure
515
11-24. Electrical
Propeller Deicing System
11-51
cjS~echcraft
BARON 55 AND 58
SHOP MANUAL
TROUBLESHOOTING
WINDSHIELD HEATER SYSTEM
Trouble
Probable Cause
1.Windshield heater inoperative,
Loose connections
Remarks
broken
wires.
Check for loose connections.
Check for continuity between
components, isolate damage and
b. Defective WSHLD switch.
b.
Replace
stuck in
c.
Replace relay.
temperature controller
d.
Replace
e.
Replace heater.
a.
Replace
b.
Replace relay
a.
or
a.
repair.
c.
Windshield heater
the open
position.
d. Defective
2. Windshield heater will not
cycle
off.
relay
switch.
e.
Damaged windshield
a.
Defective temperature controller.
b. Windshield heater
the closed position.
To prevent damage to the brushes, the brush block
assembly should be angled in such a manner that
the brushes contact the slip ring at an angle of
heater.
relay
stuck in
Timing
Sequence
approximately 2" from perpendicular, as measured
toward the direction of the slip ring rotation. Refer to
Figure 11-14. A dial indicator gage may be used to
Timer
On
controller.
controller.
Areas of Prop
Deicer Heated
Pin
30
B
sec.
check the amount of slip ring runout (wobble) in
relation to the brush block. If the total runout over
360 degrees of rotation exceeds .005 inch, or over
Pin
A
sec.
Pin
30
any 4-inch are exceeds .002 inch, the slip ring should
be aligned by adding shims between the slip ring and
its mounting surface. To avoid error in the gage
D
sec.
Right Engine prop,
outboard halves
Pin
30
Right Engine prop,
C
sec.
inboard halves
readings during such a check, slowly
ring while pushing in on the propeller
out of the thrust bearings.
rotate the
to take
slip
the play
After the brushes have been installed, the airplane
should be flown for at least one hour before the
system is energized for a period longer than that
required
for the normal installation checkout. This will allow the
brushes to set and
a
film to form
on
the
slip ring.
ELECTRIC PROPELLER DEICER TIMER
CHECK (GOODYEAR)
The deicer timer, located in the pilot’s compartment
the left hand side of the firewall, can be checked
of two methods.
11-52
Left Engine prop,
inboard halves
The second method of checking the timer is to turn on
the system and, following the above sequence, feel
the sections on the propeller iceguard to see if
they
are
heating
in the proper order.
NOTE
The timer does not reposition itself when
the system is shut off; therefore, when
the timer is turned on, the cycling will
start where it left off on the previous
operation.
on
by
Apply power to the plug attached
to the timer. Check the DC voltage to the ground from
the pins on the timer. Each pin should read 24 volts in
the following sequence:
one
30
Left Engine prop,
outboardhalves
ELECTRIC PROPELLER DEICING
(GOODRICH) CTE-938, TE-943 THRU
TE-11S1, THI1 THRU TH-1230, TC-1608
THRU TC-2418, TC~2420 THRU TC-2449)
The electric propeller deicer system includes an electrically heated boot for each propeller blade, brush
515
I
C~eechcraft
BARON 55 AND 58
SHOP MANUAL
assemblies, slip rings,
on-off switch
on
an
ammeter, timer and
th LH instrument
switch is turned on, the ammeter
subpanel.
on
an
When the
the ammeter
on
the LH
subpanel
will
register
the LH instrument
subpanel registers the amount of current (14 to 18
amperes) passing through the system. If the current
rises above the switch limit, an integral circuit breaker
ELECTRIC PROPELLER DNCER BRUSH
will cut off the power to the timer. The current flows
from the timer in the RH wing center section to the
TH-1230, TC-1608 THRU TC-2418,
TC-2420 THRU TC-2449)
brush
assembly
mounted
and is conducted
by
front of the
engine case
assembly to the slip
spinner backing plate. The slip
on
the brush
rings installed on the
rings distribute current to the deicer boot on the propeller blades. Heat from the boots reduces the grip of
the ice, which is then removed by the centrifugal effect
of propeller rotation and the blast of the air stream.
Power to the two heating elements on each blade is
cycled by the timer to the outboard and inboard heating elements in the following sequence; RH outboard,
RH inboard, LH outboard, LH inboard. Since each of
these phases is 30 seconds in duration, the timer
makes a complete cycle every two minutes. Whenever the timer switches to the next phase of operation,
REPLACEMENT (GOODRICH) (TE-938,
TE-943 THRU TE-1181, TH-I THRU
Check brush wear by inserting a piece of safety
a´•
Wire into the holes above each brush assembly block.
If the wire will insert more than 17/32 inch it is time to
’eplace the brushes. Refer to Figure 11-26.
b.
Disconnect the
brush
assembly
cannon plug and remove the
from the bracket. Refer to Figure
11-28.
Secure brushes in place before removing the brush assembly to prevent
breaking reusable brushes during and
after removal. Refer to Figure 11-27.
1
o
O
ROTATION
2"
I
17/32"
MAX
THRUST BEARING
PLATE
Figure
615
11-25.
I
BRUSH BLOCK
ASSY
Propeller
Deicer Brush Block
Installation
I
NOTE
SLIP RING ASSY
1/32 MIN.
3/32 MAX.
a
momentary deflection.
Figure
1.1-26.
Determining
Delcer Brush Wear
11-53
clSeechcraft
BARON 55 AND 58
SHOP MANUAL
Remove the
c.
screws
attaching
the cannon
plug
NOTE
to
the brush holder, then disassemble the brush holder
When
replacingbrushes or brush
retainer assemblies, always install new
by pulling the guide approximately 1/4 inch toward the
cannon IJluy
the plrls,
Refer ro
to rlgure
plug to ulst~rlyays
disengage Irlt!
pins. nerer
ll~;ll;c;erugiF
iv
springs.
h.
d.
Remove the
brush
plug, brushes, and springs from the
holder, then slide the springs off the brushes.
Unsolder the wires for the brushes
e.
replaced, noting which pin
correspond to.
f.
on
the
on
cannon
new
brush to the appro-
plug, holding the "wicking"
to
1/8-
inch maximum,
g. Set the springs in the holes of the larger block and
insert the brush rods enough to partially compress the
springs. Make
certain that
a
side load is not
applied to
from being
the brushes. This prevents the brush leads
pinched or damaged. Slip the smaller block
brushes and onto the larger block.
RUBBER
and that the brush wires must not be crossed to
proper deicer operation.
assure
NOTE
Solder both wires from the
priate pins
the
being
plug they
Install the cannon plug on the brush block with the
attaching screws and washers. Note that the guide pin
of the plug must be toward the brush support block
over
the
Secure brushes in the brush holder to
prevent breakage during assembly and
installation. Refer to Figure 11-27.
1
i.
Check the amount of brush protrusion from the
block. Brushes should protrude from 7/16 to 9/16 inch.
If the brushes protrude less than 7/16 inch, the brush
leads should be untwisted to lengthen. If this distance
is more than 9/16 inch, the leads should be twisted to
shorten. Check the brushes for free sliding action.
Refer to Figure 11-27.
BANDS AND
5
CARDBOARD FOR
HOLDING BRUSHES
BRUSH BLOCK
SHIM HERE
MOUNTING
BRACKET
7/16 TO 9/16
i~-
-~7
c-----------~
BRUSH
PROTRUSION
c-,,
,’i
i.
2.
3.
4.
5.
CANNON PLUG
SUPPORT BLOCK
BRUSH SPRING
BRUSH
GUIDE BLOCK
MOUNTING
ICI[WI
CeYUOQ~I.
I
Figure
11-54
11-27. Deicer Brush Block
Assembly
figure 11-28. Propeller Delcer Brush Assembly
515
C~3eechcraft
BARON 55 AND 58
SHOP MANUAL
i.
Place the brush block assembly on the
mounting
bracket and insert the mounting screws through both
the block and bracket. Refer to Figure 11-27.
k.
Before
installing the retainer nuts, make sure that
the brushes are aligned with the slip rings such that
the entire brush face contacts the
copper rings. If the
brushes do not align with the slip rings throughout the
entire 360 degrees of slip ring rotation, install shims
(P/N 1 E 1157) between the brush holder and the
mount until the brushes are properly aligned with the
approximate center of the copper ring.
i.
Install the
retaining washers and nuts, making certain that 1/32 to 3/32 inch is maintained between the
brush block and slip ring surface. To prevent damage
to the brushes, the brush block assembly should be
angled in such a manner that the brushes contact the
slip ring
from
I
of
at an
angle
perpendicular,
slip ring
approximately
two
degrees
measured toward the direction
rotation. Refer to Figure 11-25.
Connect and
m.
of
as
safety
wire the cannon
plug,
To
n.
of the
preclude arcing caused by the rough surfaces
new brushes, the engine should be operated for
at least five hours before the deicer
This does not
on.
tem
performed
apply
while the
to
system is turned
ground checks of the sys-
engine
is not
running.
REPLACEMENT OF BRUSH BLOCK
ASSEMBLY WITH MODULAR BRUSH
BLOCKASSEMBLY (GOODRICH) (78-938,
TE-943 THRU
TE-1181, TH-1 THRU
TH-1230, TC-1608 THRU TC-2418,
TC-2420 THRU
plastic housing
TC-2449)
with
These modular units
spacers to
are
integral
brush and spring.
stacked with the appropriate
an
produce the assemblies. Screws
together.
are
used
to hold the modules and spacers
To
replace brush blocks with modular brush blocks
contact
Authorized BEECHCRAFT Parts Outlet
and request the BEECHCRAFT Kit applicable to the
specific installation.
515
an
THRU
TE-1181, TH-I THRU TH-1230,
TC-1608 THRU TC-2418, TC-2420 THRU
TC-2449)
Experience in the field has often indicated that the
timer is considered defective when the source of the
Trouble lies elsewhere. For this reason, the following
test should be performed before the timer is removed
as
defecti~e:
With the wiring harness disconnected at the timer
and the deicer switch in the ON position, check the
voltage from pin B of the harness plug to ground. If no
a~
voltage is present, the timer is NOT at fault; however,
if system voltage is present at pin B, check the circuit
from harness plug pin G to ground with an ohmmeter.
If no circuit is indicated, the fault is in the ground lead
rather than the timer. If the ground connection is open,
the timer step switch will not change position.
b´•
After the
checked,
ground
and power circuits have been
wire between pin B of the
and terminal B of the connector plug
connecta
timer
jumper
receptacle
pin G on the timer receptacle to ground. With
the deicing system switch ON, check the voltage to
ground from pin B of the timer. The voltmeter should
indicate approximately 24 volts when the airplane battery supply is being used. Next, check the DC voltage
fO S’OU"d from pins C, D, E, and F, the points at which
the system voltage is impressed in sequence to cycle
and from
power to the propeller deicers. Each of the
should read 24 volts in the following sequence:
Modular brush assemblies were developed to replace
brush block assemblies. Each module brush assembly
is made up of three modules. Each module consists of
a
ELECTRIC PiriOPELLER DEICER TIMER
CHECK (GOODRICH) (TE-938, TE-943
Timing
Sequence
Timer
On
Pin
30
C
sec,
Pin
D
sec.
Pin
E
sec.
Pin
F
sec.
30
30
30
plugs
Areas of Prop
Deicer Heated
Right Engine prop,
outboard halves
Right Engine prop,
inboard halves
Left Engine prop,
outboard halves
Left Engine prop,
inboard halves
11-55
Ci~eechcraft
BARON 55 AND 58
SHOP MANUAL
NOTE
I
The timer does not reposition itself to
pin C when the system is turned
off, but will begin its cycling at the same
start at
position
in which it
wU´•,.,
WARRIING
I
Before
moving the propeller, make
certain that the ignition switch is off
and that the engine has cooled com-
when last turned
off. Cycling will then proceed in the order
of C, D, E, and F as before.
was
pletely. There
Is
always
danger
some
After
a voltage reading of 24 volts DC is
obtained,
hold the voltmeter probe on the pin until the
voltage
drops to zero before moving the probe on to the next
pin in the sequence noted above. After the correctness
of the
turn the
cycling sequence has
deicing system switch OFF
been established,
at the
beginning
of
of the "on-time"
CONTINUIP/ TEST (GOODRICH) (TE-938,
TE-943 THRU TE-1181, TH-I THRU
TH-1231, TC-1608 THRU TC-2418,
TC-2420 THRU TC-2449)
periods and record the letter of
the pin at which the voltage supply is
present to facilitate performance of the following test.
After
HEAT TEST
Pin C of the
prop boot on the
plug to the outboard terminal
right engine.
of
one
b.
plug to the inboard terminal
right engine.
of
one
terminal of
one
one
removing
meter to check
the
plug from the timer,
continuity from:
a.
THRU
(OiOODRiON) (TE-938, TE-943
TE- 1181, TH-1 THRU TH-1230,
Pin D of the
TC-1608 THRU TC-2418, TC-2420 THRU
prop boot
TC-2449)
c.
Before this test
can
be
performed, the jumper wire
installed for the timer test must be removed
connector
plug
can
so
that the
be
replaced in the timer receprequired to perform this test, one
tacle. Two men are
in the cockpit to monitor the ammeter while the other
checks the deicer boots. The man in the cockpit turns
the deicer system switch ON while the man outside
Pin E of the
prop boot
d’
f~
on
plug to the outboard
engine.
plug to the inboard terminal
engine.
plug
to
Ground terminal of
ground.
one
prop boot
on
the
g. Ground terminal of
ine to ground.
the proper readings (14 to 18 amperes)
throughout the
timing sequence. The ammeter needle should deflect
ELECTRIC PROPELLER DEICING
of his hands to check the proper heating
sequence of
the propeller deicer areas. If
any irregularities are
detected,
continuity check should be performed on
from
the timer to the brush block holders
wiring
and the propeller deicer terminal connections.
a
the
CAUTION
While following the instructions of the
"HEAT TEST’ section, move the propeller back and forth to prevent arcing
between the brushes and slip ring,
11-56
right
eng-
ground.
feels the deicer boots to see if they are heating
properly. The man in the cockpit observes the ammeter for
every 30 seconds in response to the switching action
of the timer. Each time this occurs, the man in the
cockpit must notify the man inspecting the propeller
deicer boot so that the latter can change the
position
of one
the left
Pin G of the
ine to
ohm-
the left
on
Pin F of the
P’OP boot
e´•
the
on
use an
one
prop boot
on
the left eng-
(GOODRICH) (HOT PROP) (TE-1182 AND
AFTER, TH-1231 THRU TH-1396 EXCEPT
TH-1389’ TC-2419, TC-2450 AND AFTER)
Airplanes with
single-element
the above serials are equipped with
deicer boots. The deice boot incorporates a ribbon element which replaces a wire element.
Power to the boot is cycled in 90-second
phases
instead of 30-second phases. The leads out of the
deice boot are reduced from 3 to 2. The
slip ring
mounts in the same location but also reduces from 3
rings to 2 rings. The brush block mounts on the same
bracket, but instead of 3 brushes, there are 2 modular
brushes. A smaller timer is used and requires new
mounting holes. The wiring harness on the modular
brush assembly has 2 wires. Refer to the BEECHCRAFT Parts
to the
Catalog
for BF Goodrich Kit
applicable
specific installation.
515
~eechcraft
BARON 55 AND 58
SHOP MANUAL
ELECTRIC PROPELLER DEICER
MODULAR BRUSH REPLACEMENT
I
NOTE
During measurement only 1/16 inch of
brush should protrude from the brush
module, this being the normal protrusion
brush Is installed on the air-
(GOODRICH) (78-1182 AND AF~ER,
TH-1231 THRU TH-1396 EXCEPT
TH-1389, TC-~419, TC-2450 AND AFTER~
The modular brush
assembly is made up of two modules. Each module consists of a plastic housing with
integral
brush and
spring. The modular units are
spacer and are held together with
screws. When a brush wears out, the entire module
must be replaced. A brush module is considered to be
worn out when only 3/8 inch of material remains.
an
stacked with
a
Brush wear is determined by inserting a pin into a hole
in the back of the brush module as shown. Refer to
Figure 11-29. On all rodless brushes, the brush module must be replaced when the dimension shown is
1-7/64 ~1/32 inches. Refer to Figure 11-29.
Disconnect the wire harness terminals at the terminal screws of the modular units that make
up the
brush assembly.
a.
b.
Remove the screws, nuts, and washers
the modular units to the mounting bracket.
When replacing propeller deicer
brushes, all attaching hardware must be
torgued to
than 18
inch-pounds
damaging the brush
no more
in order to avoid
modules.
c.
Remove the
assembly retaining
screws
securing
and sepa-
rate the modules and spacer.
d.
Replace
e.
Restack the modules and spacer.
each module with another of the same
number.
The part number is etched into the surpart
face of the plastic~housing.
f.
Install the assembly screws so that the screw head
fits in the recess in the spacer. Place the flat washer
between the star washer and modular
housing and
install the retaining nut. Make sure the
assembly is
"square" before tightening
place.
the
assembly
screws
in
Place the modular units on the mounting screws
through the modules and bracket. One washer fits
under the head of the screw and one under the retaing.
ing
nut.
h.
Before
installing the retainer nuts, make sure
are aligned with the slip rings such
the brushes
1
that
that
the entire brush face contacts the copper
rings. If the
brushes do not align with the slip rings throughout the
entire 360 degrees of slip ring rotation, install shims
7/
MAX.
(P/N 161157) between the brush module spacer and
mounting bracket until the brushes are properly
aligned with the approximate center of the copper ring.
the
90-251-27
NO’IE
During
the
measurement
only
1/16 inch of brush should be allowed to protrude from the brush
module.
i.
Install the retaining washers and nuts, making certain that 1/32 to 3/32 inch is maintained between the
brush modules and the slip ring surface. To
prevent
I
Figure
615
11-29. Brush Wear On Modular Brush
damage to the brushes, the brush modules should be
angled so that the brushes contact the slip rings at an
angle of approximately two degrees from perpendicular, as measured toward the direction of slip ring rotation, as shown. Refer to Figure 11-30.
11-57
cl~eechcfaft
BARON 55 AND 58
SHOP MANUAL
j. Reconnect the terminals of the airplane system
wire harness to the same designated terminals of the
modular brush assembly.
b.
After the
checked,
ground
connect
a
and power circuits have been
wire between pin B of the
jumper
timer
receptacle and terminal B of the connector plug,
pin G on the timer receptacle to ground. With
the deicing system switch ON, check the voltage to
ground from pin B of the timer. The voltmeter should
indicate approximately 24 volts de when the airplane
battery supply is being used. Next, check the voltage
to ground from pins D and F, the points at which the
System voltage is impressed in sequence to cycle
power to the LH and RH propeller deicers. The prese"ce of 24 vdc system voltage should alternate at
pins
and from
ELECTRIC PROPELLER DEICER TIMER
CHECK (GOODRICH) (TE- 1182 AND
AFTER, TH-1231 THRU TH-1396 EXCEPT
TH-1389, TC-2419, TC-2450 AND ATTER)
Experience
in the field has indicated that often the
timer is considered
inoperable when the
trouble is elsewhere. For this reason, the
should be performed before the timer is
source
of the
following test
judged to be
D a"d F for 90 seconds in duration
as
the timer
inoperable,
cycles.
With the timer harness plug disconnected and the
a.
deicer switch in the ON position, check for voltage
from pin B of the plug to ground. If no voltage is
voltage reading of 24 volts DC is obtained,
probe on the pin until the voltage
d’OpS to zero before moving the probe on to the next
Pi" in the sequence. Refer to Figure 11-40. After the
co"ect"ess of the cycling sequence has been established, turn the deicing system switch OFF at the
beginning of one of the "on-time" periods and record
the letter of the pin at which the voltage supply is
present to facilitate performance of the following test.
present, the timer is not defective check the power
supply. However, if system voltage a present at pin B,
check the circuit from the harness to ground with an
ohmmeter. If there is no continuity, the fault is in the
ground circuit
rather than the timer. If the
cult is open. the timer will not cycle.
ground
cir-
C´•
After
a
hold the voltmeter
HEAT TEST
(GOODRICH) (TE- 1132 AND
AFTER, TH-1231 THRU TH-1396 EXCEPT
TH-1339, TC-2419, TC-2450 AND AFTER)
FWD
Remove the jumper wires that were installed for
a.
the timer test and reconnect the timer receptacle. Two
SLIP RING ROTATION
required to perform this test, one man in the
to operate the propeller deice switch and
observe the propeller deice ammeter, the other on the
ground checking the deice boots for proper heating.
men are
SLIP RING ASSY
cockpit
t
-r
2"
b.
While the person in the cockpit observes the
a reading of 14 to 18 amps, the
person
on the ground checks for a rise in heat on each
propeller deice boot for approximately 90 seconds on
ammeter for
each sid‘e.
If either boot fails to heat, check the circuit
between the timer and the propeller deice boot for
c.
continuity.
BRUSH MODULE ASSY
Figure
11-30. Modular Brush
Installation
11-58
Assembly
t~´•-?
While following the instructions of the
"HEAT TEST’ section, move the propeller back and forth to prevent arcing
between the brushes and
slip ring.
515
BARON 55 AND 58
SHOP MANLIAL
I
WARNING
w~.I.,
I
b.
Remove the six slip
c.
Removethe
and washers.
stip ring.
PROPELLER SLIP RING INSTALLATION
Before moving the propeller, make
certain that the magneto/start switch
is off and that the engine has cooled
completely. There is always some
danger of a cylinder firing when the
propeller is moved.
(GOODRICH)
head.
AND AFTER, TH-1231 THRU TH-1396
EXCEPT TH-1389, TC-2419, TC-2450 AND
AFTER)
c.
After
removing
meter to check
a.
b.
d.
the
on
plug
plug
to the terminal of the
propeller
engine.
to
to
boot
propeller
on
the
right
ground.
The slip rings may be properly aligned as
described in SLIP RING ALIGNMENT in this section.
BRUSH BLOCKJ/MODULE RESISTANCE
CHECK (GOODRICH)
boot
on
the left
ground.
the resistance from the face of the brush to its termi-
tacting
b.
To check for incorrect resistance
or
the presence
E, and F of the harness plug) to ground with
a
low
range ohmmeter.
If the resultant
readings
individually.
readings
d.
in the first check
are
in the second check
damaged
are
a
megohms after
one
tester
I
preceding adjustments may affect
the clearance between the brush block/
slip rings. Consequently,
slip ring alignment, a check should
module and
after
be made to ascertain that
a
distance
from 1/32 to 3/32 inch is maintained
between the brush block/module and
slip ring surface.
Refer to
SLIP RING ALIGNMENT
(GOODRICH)
The
515
a
The
replaced.
Remove the propeller as described in Section 7,
REMOVING THE PROPELLER.
minute. Use
500-VDC, 1000-megohm capacity.
PROPELLER SLIP RING REMOVAL
a.
0.013 ohms,
NOTE
also off, the deicer
and must be
over
of excessive resistance.
Check the resistance between the terminal studs
having
not within the
readings
measures
cause
If the resistance is infinite, locate and correct the
or ground, or else replace the brush.
less than .5
Individual boot resis-
limits but those in the second check are, the
probably in the brush-to-slip ring area. If the
concerned is
the
and/or connector pins. This resistance should not be
measure
trouble is
accepted
repair
open circuit
tance should measure between 4.58 and 5.26 ohms.
If the
If this resistance
not 1.55 to 1.78
are
ohms, disconnect the deicer lead straps to
c.
a low range ohmmeter. The probe conthe brush should have a minimum contact sur-
locate and
(GOODR/CH)
heater resistance
open circuit, a short, or high resisor brush module, measure
face of 1/16 square inch.
of a short or open circuit at the brush-to-slip ring contact, disconnect the harness at the timer and check
the resistance from each deicer circuit lead (pins C, D,
b.
an
tance in the brush block
c.
a.
To check for
I
nal stud with
propeller
BRUSH-TO-SLIP RING RESISTANCE
TEST
Install the propeller as described in Section 7,
INSTALLING THE PROPELLER.
a.
ground
Ground terminal of the
engine
b.
d.
propeller
Ground terminal of the
to
ohm-
use an
of the
plug to the terminal
right engine.
the left
Pin G of the
engine
e.
on
Pin F of the
deice boot
c.
plug from the timer,
continuity from:
Pin D of the
deice boot
(GOODRICH) (TE- 1182
the
I
Place the slip ring in place with AN936B416 star
a.
washers between the slip ring and the spinner bulk-
Torque the six slip ring attach bolts to approximately 25 inch-pounds being careful not to compress
the star washers too much, which provides slip ring
alignment adjustment.
CONTINUITY TEST
I
ring attach bolts
Figure
11-30.
I
(GOODRICH)
slip rings are properly aligned when they run in a
true plane relative to the brush block/module. This
condition may be checked by attaching a dial indicator
11-59
~eechcraft
BARON 55 AND 58
SHOP MANUAL
gage to the engine in such a manner that a reading of
the slip ring runout may be obtained. To avoid error in
readings, rotate the slip rings slowly while pushing in
the
propeller to take the play out of the thrust bearIf the total runout over 360 degrees of rotation
exceeds 0.005 inch, the slip rings should be aligned
as follows:
on
ings.
PROPELLER DEICER BOOT REMOVAL
(GOODRICH)
a´•
Remove the
b~
Disconnect the deicer boot leads from the spinner
bulkhead.
Remove the
c.
a.
Approximately
made to correct
0.012 inch
adjustment may be
the slip ring runout by varying the tora
cue on the attachment bolts. Using the dial indicator to
follow the points of maximum deviation, adjust the slip
ring assembly to the prescribed runout limits by varying the torque of the mounting bolts as required, within
a range of 25 to 65 inch-pounds.
b.
If more than 0.012 inch of adjustment is required
alignment, the slip ring assembly may be shimmed
to within the prescribed limits for true running by the
addition of AN960C416L washers on the mounting
bolts between the slip ring assembly and the spinner
propeller spinner.
spinner bulkhead
peller hub.
clip securing the lead strap to the
clamp securing it to the pro-
and the
d~
Using methyl ethyl ketone or toluol (19, 20 Consumable Materials Chart, Section 2) to soften the
adhesion line between the boot and the blade, loosen
one corner
grip pliers
of the boot
or a
sufficiently to grasp
I
it with vise
similar tool.
for
CAUTION
Unless the boot being removed is to be
scrapped, cushion the jaws of any pulling tool to prevent damaging the boot
surface.
bulkhead. If necessary fabricate thinner shims to the
AN960 size.
I
SLIP RING MACHINING
Slip rings
faces, but
are
and restored to
a.
(GOODRICH)
which have
roughened
structurally sound,
damaged
a
slip ring assembly from the airplane
lathe. Position it concentrically in the
Take light cuts for
deeper than required to
or
runout
Remove the
remaining
with toluol
adhesive from the boot and
methyl ethyl ketone.
or
than 0.0005 inch. The contact surfaces of the
rings must have a finish of 29-35 microinches.
Deburr the
slip ring edges
align.
slip
and reinstall in the air-
NOTE
If, the solder or braze connection on the
underside of the slip ring is exposed by
machining, replacement of the slip ring
assembly will be necessary.
PROPELLER DEICER BOOT
INSTALLATION (GOODRICH)
I
over a
If necessary, undercut the insulation between the
slip rings to a depth of 0.020 to 0.030 inch below the
contact surface of the slip rings. In this operation, the
width of the slip ring MUST NOT be reduced by more
11-60
f´•
a
c.
and
vent to soften the adhesive.
remove
Deviation from flat is not to exceed 0.002 inch
4-inch are.
plane
the
propeller blade
smooth finish and cut no
surface damage. The
contact surfaces of the three slip rings must be parallel within 0.005 inch, and flat within 0.005 inch overall.
d.
Apply a slow, steady pull on the boot to pull it off
propeller surface while continuing to use the sol-
e.
lathe, with not over 0.002 inch of wobble
over 360 degrees of rotation.
b.
sur-
be machined
serviceability,
Remove the
and mount it in
or
can
Position the deicer boot on the propeller blade so
a.
that its centerline at the inboard end is adjacent to the
split
in the
propeller blade clamp and 1 inch outboard
clamp, and the centerline at the outboard end
falls on the blade leading edge. Be sure the lead strap
is in the proper position to be clamped to the blade
retaining clamp.
of the
b. Mask off an area approximately 1/2 inch from the
end of each side of the boot. Refer to Figure 11-31.
Remove the deicer boot and strip any paint in the
area from the retaining clamp outboard.
Clean the area thoroughly with methyl ethyl ketone or
c.
masked
(Item 19 or 20, Consumable Materials Chart).
cleaning, wipe the solvent off quickly with a
clean, dry, lint-free cloth to avoid leaving a film.
toluol
For final
515
I
~iS)eechcraft
BARON 55 AND 58
SHOP MANUAL
g. Position the deicer boot on the propeller, starting
1 inch from the blade retaining clamp, making sure the
The metal and rubber
thoroughly
clean to
parts
assure
lead strap is in position to clamp to the blade retaining
clamp. Moisten the cement lightly with methyl ethyl
must be
maximum
ketone
toluol and tack the boot center line to the
If the centerline of the boot deviates from the blade leading edge, pull up with a quick
adhesion,
d.
Moisten
a
blade
clean cloth with
toluol and clean the
or
motion and
replace properly.
to avoid contami-
te’line with
a
firmly along the cenFigure 11-32.
1
area.
mix EC1403 cement (Item 60, ConMaterials Chart, Section 2) and apply one
even brush coat to the propeller blade. Allow
cement to dry for at least one hour at 40"F or above
when the relative humidity is less than 75% or two
elbamuseht
hours if the
apply
humidity
Never
use a
metal
this purpose, for
is between 75% and 90%. Do not
humidity is higher than
the cement if the relative
h.
wooden roller for
or
they
heating elements
would
damage
the
in the deicer boot.
Gradually tilting the roller,
work the boot carefully
each side of the blade