Improving Business Aircraft Performance
INSTALLATION INSTRUCTIONS
Raisbeck Engineering Nacelle Wing Lockers
for the Beechcraft Super King Air
200/200C/200T/200CT/A200/A200CT/
B200/B200C/B200T/B200CT/B200GT/B200CGT
Raisbeck Engineering Document 87-1007
Advanced Technology Performance and
Environmental Improvement Systems
for Your KING AIR and SUPER KING AIR
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
INSTALLATION INSTRUCTIONS
RAISBECK ENGINEERING NACELLE WING LOCKERS FOR THE
BEECHCRAFT SUPER KING AIR 200/200C/200T/200CT/A200/A200CT/
B200/B200C/B200T/B200CT/B200GT/B200CGT
RAISBECK ENGINEERING DOCUMENT 87-1007
ORIGINAL ISSUE:
REVISION A:
REVISION B:
REVISION C:
REVISION D:
REVISION E:
REVISION F:
REVISION G:
REVISION H:
REVISION I:
REVISION J:
REVISION K:
REVISION L:
REVISION M:
June 15, 1987
August 6, 1987
November 24, 1987
November 7, 1987
February 2, 1989
May 5, 1989
October 9, 1995
September 23, 1999
March 29, 2007
November 5, 2007
June 10, 2011
May 4, 2012
March 26, 2013
November 1, 2017
PREPARED BY:
D, Thorsen
CHECKED BY:
M. Lizarr
APPROVED BY:
E. Murvine
Revision M: November 1, 2017
i
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
LOG OF REVISIONS
REV
DESCRIPTION
DATE
K
UPDATED INSTALLATION MANUAL FORMATTING TO
CURRENT FORMATTING STANDARDS
MAY 4, 2012
ADDED LOG OF REVISIONS PAGE
TABLE OF CONTENTS – UPDATED PAGE NUMBERS
ACCORDINGLY
SECTION 3.1 - REVISED “REVISION” LINE FROM “I” TO
“LATEST APPROVED”
L
INACTIVE FOR FUTURE DESIGN
MARCH 26, 2013
M
RE-ACTIVATED INSTALLATION INSTRUCTIONS.
ADDED FIGURES FROM REV K THAT WERE MISTAKENLY
OMITTED FROM REV L.
SEE DCN M FOR DETAILS.
NOVEMBER 1, 2017
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ii
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
TABLE OF CONTENTS
SECTION
PAGE
1 INTRODUCTION ..............................................................................................................................1
2 AFT NACELLE STOWAGE COMPARTMENT DESCRIPTION ...............................................1
3 REQUIRED DOCUMENTATION ...................................................................................................... 2
3.1
Raisbeck Engineering Supplied ..................................................................................... 2
3.2
Customer/installer Supplied ............................................................................................ 2
4 REQUIRED AIRCRAFT CONFIGURATION ................................................................................... 2
5 KIT CONTENTS .................................................................................................................................... 3
6 SPECIALIZED TOOLING REQUIRED ............................................................................................. 3
7 AFT NACELLE STOWAGE COMPARTMENT INSTALLATION ................................................. 3
7.1
Aft Upper Nacelle Removal ............................................................................................. 3
7.2
Aft Lower Nacelle Fairing Removal ................................................................................ 3
7.3
Aft Attach Structure Installation ..................................................................................... 4
7.3.1
Outboard Structure Installation ................................................................................. 4
7.3.2
Inboard Structure Installation .................................................................................... 6
7.4
Wing Locker Location ....................................................................................................... 8
7.5
Aft Lower Nacelle Fairing Installation ....................................................................... 10
7.6
Aft Attach Structure Final Installation ...................................................................... 11
7.7
Wing Locker Forward Attach Installation ................................................................. 11
7.7.1
Inboard and Outboard Side Forward Fairing Installation ................................ 11
7.7.2
Final Forward Fairing Installation .......................................................................... 13
7.7.3
Final Installation .......................................................................................................... 13
7.7.4
Final Flap Installation ............................................................................................... 14
8 PAINT PREPARATION..................................................................................................................... 14
8.1
Anti-Static Treatment ..................................................................................................... 15
9 RETURN AIRCRAFT TO SERVICE .............................................................................................. 16
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
1 INTRODUCTION
This document is intended to provide detailed instructions for the installation of the Raisbeck
Engineering Dual Aft Nacelle Stowage Compartment on Beechcraft Super KING AIR
200//200C/200T/200CT/A200/A200CT/B200/B200C/B200T/B200CT/B200GT/B200CGT
aircraft. The instructions are presented in a recommended sequence. However, some of the
activities presented may be accomplished concurrently to suit the installers schedule.
THE RAISBECK ENGINEERING DUAL AFT NACELLE STOWAGE COMPARTMENT
HAS BEEN APPROVED BY THE FEDERAL AVIATION ADMINISTRATION (FAA)
UNDER SUPPLEMENTAL TYPE CERTIFICATE (STC) SA3857NM.
THE INSTALLATION OF THIS SYSTEM MUST CONFORM TO THE FAA APPROVED
RAISBECK ENGINEERING INSTALLATION FIGURES AND THE INSTRUCTIONS
CONTAINED IN THIS DOCUMENT.
CONFORMITY VERIFICATION OF THE INSTALLED SYSTEM TO THE RAISBECK
ENGINEERING INSTALLATION FIGURES AND THE INSTRUCTIONS IS THE
RESPONSIBILITY OF THE INSTALLATION FACILITY.
2 AFT NACELLE STOWAGE COMPARTMENT DESCRIPTION
The Raisbeck Engineering Dual Aft Nacelle Stowage Compartments are specifically designed
to transport long and otherwise unwieldy cargo (skis, golf bags, guns, etc.) which presently
may not be possible.
The aft nacelle upper skin is removed and replaced with the wing locker, which extends aft
above the flap. The aft nacelle lower fairing on the flap is replaced with a fairing that matches
the wing lockers contour and the upper surface of the wing in the flap well area is reinforced
for the wing locker aft attachment.
Revision M: November 1, 2017
87-1007
Page 1
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
3 REQUIRED DOCUMENTATION
3.1
Raisbeck Engineering Supplied
The following document of the correct revision will be supplied as part of the kit:
NUMBER
REVISION
NAME
87-1007
Latest Approved
Installation Instructions
3.2
Customer/installer Supplied
The following documents of the latest revision in effect at the time of kit installation
shall be supplied by the customer or the installer.
101-590010-19
Beechcraft Super KING AIR 200/200C/200T/200CT/A200/A200CT/
B200/B200C/B200T/B200CT/B200GT/B200CGT Maintenance Manual
EA -AC 43.13
Acceptable Methods, Techniques and Practices for Aircraft
Alteration, Inspection and Repair
4 REQUIRED AIRCRAFT CONFIGURATION
NOTE:
AIRCRAFT MODELS BP-1, BP-19 THROUGH BP-22, BP-24 and AFTER, BC-1
AND AFTER BD-1 AND AFTER, MUST COMPLY WITH ONE OF THE
FOLLOWING BEECH DRAWINGS PRIOR TO INCORPORATION ON THESE
INSTRUCTIONS:
101-005008
101-005016
101-005019
101-005001
101-005002
101-005003
101-005004
117-005007
101-005059
127-005001
127-005002
AIRCRAFT MUST MEET TYPE DESIGN FOR A200 PRIOR TO THIS INSTALLATION.
CONTACT RAYTHEON AIRCRAFT COMPANY FOR TYPE DESIGN INFORMATION.
Revision M: November 1, 2017
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
5 KIT CONTENTS
The 89-1001-1 kit is contained and shipped in two boxes. Each box contains a wing locker,
aft fairing, detail parts and hardware.
6 SPECIALIZED TOOLING REQUIRED
In addition to standard aircraft technician tools, the following specialized tools will be required:
Any Cherry Max riveter
Any Cherry bulb rivet puller
7 AFT NACELLE STOWAGE COMPARTMENT INSTALLATION
REF. FIGURE I
The installation of the Aft Nacelle Stowage Compartment is defined in this section. Refer to
Figure 1 for general arrangement of the components.
The operations defined here are those necessary to rework the left nacelle. Operations for the
right nacelle are the same except where opposite parts may be encountered.
7.1 Aft Upper Nacelle Removal
REF. FIGURE 2
1)
Remove the existing rivets in the forward row of the aft nacelle skin.
NOTE:
2)
Ribs on the aft nacelle skin are not attached to the sub-structure
and can be removed with the skin without drilling out the rib attach
fasteners.
Remove and discard the aft nacelle skin by cutting the skin 0.06 to 0.12 inch
above the upper surface of the wing skin as shown in Section A-A.
CAUTION: MAKE THE FIRST TRIM OF THE SKIN ABOUT 2 INCHES
ABOVE THE WING TO AVOID DAMAGING THE SUBSTRUCTURE, PARTICULARLY THE FRONT SPAR AND NACELLE
ATTACHMENT STRAPS TRIM TO THE FINISHED DIMENSIONS
SHOWN AFTER THE BULK OF THE SKIN IS REMOVED AND
THE SUB-STRUCTURE CAN BE SEEN.
3)
Trim the aft portion of the nacelle skin splice flush with the aft face of the
bulkhead flange as shown.
NOTE: Do not drill the aft upper nacelle skin loose from the wing skin.
4)
7.2
Apply chemical film treatment (Alodine) and one coat of primer (MIL-PRF23377) to the bare aluminum edges of the aft nacelle skin and skin splice.
Aft Lower Nacelle Fairing Removal
REF. FIGURE 5
1)
Remove the left and right flap (Ref. Beechcraft Super King Air Maintenance
Manual). Pull the flap motor control circuit breaker.
2)
Remove and discard the existing aft lower nacelle fairing from the flap by carefully
drilling out the existing rivets.
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87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
3)
Remove fasteners from the flap trailing edge 27 places beginning with the first
fastener between 6.5 and 7.5 inches inboard of the flap outboard end as shown.
Discard existing fairing.
NOTE:
7.3
Document No. 87-1007
Do not install new fairing before accomplishing Section 6.4 of these
instructions.
Aft Attach Structure Installation
1)
See Figure 3 for general arrangement and position of top plates, doublers,
and backing plates for the structure installation.
7.3.1 Outboard Structure Installation
For a view looking down on the installation, see Detail B on Figure 4.
REF. FIGURE 4
1)
On airplanes BB-2 through BB-424 and BT-1 through BT-4,BP-1, BP-19 through BP19, BP-22, BP-24 and after,BC-1 and after and BD-1 and after only, remove the flap
asymmetry switch plate by removing the 4 attach fasteners from the trailing edge skin
panel and retain the switch and plate.
2)
Remove the fasteners attaching the existing stiffener to the trailing edge skin panel.
Remove 2 additional fasteners in the inboard and outboard trailing edge rib forward of
the stiffener.
3)
Remove and discard the existing stiffener by carefully trimming the stiffener off
at the inboard and next to the rib.
4)
Draw a line on the top of Backing Plate (85-3510-181) 0.45 inch forward of
the plate aft edge. This line will be the minimum edge margin for the location of
the aft row of fasteners in the backing plate.
5)
Position backing plate on the lower side of the skin with the outboard edge
with 0.020 inch gap at the outboard rib flange and with the line, drawn in
Step 4, showing in the center of the row of the existing holes.
6)
Drill No. 40 holes in the backing plate to match the existing row of fastener
hole locations 8 places and at the 4 holes for the asymmetry switch plate, if
existing. Remove backing plate.
7)
Draw a line on the bottom of Top Plate (85-3510-177) 0.35 inch forward of
the plate aft edge. This line will be the minimum edge margin for the location
of the aft row of fasteners in the top plate.
8)
Position top plate on the top surface of the trailing edge skin panel with tab
inboard and forward as shown in Detail B. Adjust top plate in the inboard and
outboard direction so equal edge margin will exist on the plate ends when the
existing fastener locations in the ribs are picked up. Adjust top plate in the
forward and aft direction so the line, drawn in Step 7, will show in the center
of the existing row of fastener holes in the skin. From the bottom, mark all
existing hole locations on the top plate. Remove top plate.
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87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
9)
With parts removed from the airplane, align the aft row of holes marked on
the top plate with the No. 40 holes drilled in the backing plate.
10)
From the top, mark the pilot holes in the forward row of the top plate on the
backing plate. Check the edge margin of the forward row of holes on the
backing plate.
NOTE:
If the backing plate will not have 0.45 inch edge margin for the
forward row of fasteners, move the final location of the top plate,
maintaining the inboard and outboard location, aft to obtain 0.45 inch
edge margin from the forward edge of the backing plate.
11)
With the top plate located on the backing plate so all the conditions in Steps
4) and 10) are met, drill No. 40 holes in the top plate to match the holes in
backing plate for the aft row of fasteners and the asymmetry switch plate, if
existing.
12)
Install top plate and backing plate with clecos. Drill the aft row of holes
common to the skin, top plate, and backing plate with a No. 30 drill 8 places.
If the asymmetry switch plate fastener holes exist, enlarge holes with a No.
30 drill 4 places. Remove the backing plate and sub-counter sink the top
surface of the backing plate so the plate will rest flat against the skin lower
surface and the skin dimples nest in the sub-countersink. Reinstall the top
plate and backing plate with clecos.
13)
Drill No. 40 holes in the top plate to match the existing locations in the ribs, 3
places each rib. Drill No. 40 holes in the skin and backing plate to match all
pilot holes in the top plate, 9 places. On airplanes without an asymmetry
switch plate, layout and drill No. 40 holes 4 places in the same positions
shown for the plate maintaining minimum edge margin and spacing.
14)
Remove the backing plate and locate Doubler (85-3510-183) at the inboard
end of the backing plate and with equal gap forward and aft as shown in
Detail B, View DD, and Section F-F. Drill No. 40 holes in the doubler to
match pilot hole locations in the backing plate, 7 places. Drill No. 30 holes in
the doubler to match existing hole locations in the backing plate, 4 places.
15)
Locate 4 fasteners for Screw (NAS517-2-5) maintaining minimum edge
margin and spacing. Drill No. 40 holes in the top plate, skin, and rib as shown in
Detail B.
16)
At the inboard rib locate Radius Filler (85-3510-189) as shown in View D-D.
At the outboard rib locate Radius Filler (85-3510-187) as shown in View D-D.
Drill No. 40 holes in the fillers to match existing holes in the rib.
17)
Install top plate, backing plate, doubler, and fillers on the airplane with
clecos.
18)
In this step all the remaining holes in the installation, except for the locker
attach hole, are enlarged to their final size as shown in Detail B. Because the
stack up of material is thick, carefully drill the holes perpendicular to the wing
upper surface as follows:
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
a)
Enlarge the forward row of holes to No. 30 in the top plate, skin, and
backing plate to match 4 locations.
b)
Enlarge the holes in the top plate, skin, backing plate, and doubler to No.
30 at 6 locations.
c)
Enlarge the holes to No. 30 in the top plate, skin, ribs, and radius fillers
to match the existing locations 4 places.
d)
Enlarge the holes to 0.164 (+.004 or -.000) in the top plate, skin, ribs,
and radius fillers to match the existing locations 4 places.
e)
Pilot drill the locker attach hole through the structure using a No. 40
drill. DO NOT ENLARGE LOCKER ATTACH HOLE AT THIS TIME.
19)
Countersink the upper surface of the top degrees to match Rivet
(MS20426AD4) 24 places and Screw (NAS517-2) 4 places.
20)
Remove and deburr all parts. Countersink the lower surface of the backing
plate at one location just forward of the asymmetry switch plate location so
that rivet can be double flushed.
21)
Apply a chemical film treatment (Alodine) to all bare aluminum surfaces and
one coat of primer.
22)
Install top plate and fillers on the airplane with Rivet (MS20426AD4-8) 3
places and with Screw (NAS517-2-5), Washer (AN960-8), and Nut
(NAS679A08) 4 places. Install the most forward outboard fastener, Rivet
(MS20426AD4-6).
23)
Install top plate and backing plate with Rivet (MS20426AD4-6) 6 places. On
airplanes with asymmetry switch plate, double flush the new rivet under the
plate.
24)
Install top plate, backing plate, and doubler with Rivet (MS20426AD4-10) 10
places.
25)
Install top plate, backing plate, and asymmetry switch plate with Rivet
(MS20426AD4-6) 4 places.
7.3.2 Inboard Structure Installation
For a View looking down on the installation, see Detail C on Figure 4.
REF. FIGURE 4
1)
Remove the fasteners attaching the trailing edge skin panel to the inboard
and outboard trailing edge rib forward of the stiffener, 2 places each rib shown in
Detail C.
2)
Position Top Plate (85-3510-175) on the top surface of the trailing edge skin
panel with the locker attach hole in the most forward outboard position as
shown in Detail C. Adjust top plate in the inboard and outboard direction so
Revision M: November 1, 2017
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
equal edge margin will exist on the plate ends when the existing fastener
locations in the ribs are picked up. Adjust top plate in the forward and aft
direction so the front edge is parallel to the skin lap with 0.063 inch gap
minimum and aft edge will have at least 0.35 inch edge margin when the
existing fasteners locations in the rib are picked up.
NOTE:
The -175 plate is used on the left and right installation, however, the
plate can easily be installed backwards. The plate is in its proper
position when the locker attach hole is in the most forward outboard
position.
3)
With the top plate located, drill No. 40 holes in the skin to match the pilot holes
in the plate 19 spaces.
4)
Position Backing Plate (85-3510-179) on the lower side of the skin centered
between the rib flanges and with equal edge margin for the forward and aft rows
of fasteners from the top plate.
5)
Drill No. 40 holes in the backing plate to match the holes in the top plate and
skin 19 places. Remove backing plate.
6)
Locate Doubler (85-3510-183) on the backing plate to obtain minimum edge
margin with the pilot holes in the plate and with equal gap forward and aft as
shown in Detail C, View E-E, and Section G-G. Drill No. 40 holes in the doubler
to match pilot hole locations in the backing plate, 11 places.
7)
8)
Install top plate, backing plate, and double with clecos.
Drill No. 40 holes in the top plate to match the existing locations in the ribs,
2 places each rib.
9)
At the inboard and outboard rib locate Radius Filler (85-3510-185) as shown
in View E-E. Drill NO. 40 holes in the fillers to match existing holes in the
rib, 3 places in each filler.
10)
Locate 4 fasteners for Screw (NAS517-2-5) maintaining minimum edge margin
and spacing. Drill No. 40 holes in the top plate, skin, and rib as shown in
Detail C.
11)
Install top plate, backing plate, doubler, and fillers on the airplane with clecos.
12)
In this step all the holes in the installation except for the locker attach hole
are enlarged to their final size as shown in Detail C. Because the stack up of
material is thick, carefully drill the holes perpendicular to the wing upper
surface as follows:
a)
Enlarge the forward and aft row of holes to No. 30 in the top plate, skin,
and backing plate 8 places.
b)
Enlarge the holes to No. 30 in the top plate, skin, backing plate, and
doubler 10 places.
c)
Enlarge the holes to No. 30 in the top plate, skin, ribs, and radius fillers
1 place at each rib location.
Revision M: November 1, 2017
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
d)
Enlarge the holes to 0.164 (+.004 or -.000) in the top plate, skin, ribs,
and radius fillers 2 places at each rib location.
e)
Pilot drill the locker attach hole through the structure using a No. 40
drill. DO NOT ENLARGE THE LOCKER ATTACH HOLE AT THIS TIME.
13)
Countersink the upper surface of the top plate 100 degrees to match Rivet
(MS20426AD4) 20 places and to match Screw (NAS517-2) 4 places.
14)
Remove and deburr all parts. Apply a chemical film treatment (Alodine) to all
bare aluminum surfaces and one coat of primer.
15)
Install top plate and fillers on the airplane with Rivet (MS20426AD4-8) 2
places and with Screw (NAS517-2-5), Washer (AN960-8), and Nut
(NAS679A08) 4 places.
16)
Install top plate and backing plate with Rivet (MS20426AD4-6) 10 places.
17)
Install top plate, backing plate, and doubler with Rivet (MS20426AD4-10) 10
places.
7.4 Wing Locker Location
THIS SECTION SHOULD BE CAREFULLY STUDIED FROM BEGINNING TO
END BEFORE STARTING THE WORK. THE LOCKER MUST BE PROPERLY
LOCATED BEFORE DRILLING AND TRIMMING.
1)
If airplane is equipped with the Raisbeck ENHANCED PERFORMANCE
LEADING EDGE SYSTEM, the forward inboard section of the wing locker must
be trimmed before initial fitting of the locker. The trim line can be found on the
inside surface of the locker.
NOTE:
Seal (S-3760 or OPTIONAL 85-3570) does not extend forward past
the front spar. Trim the forward inboard section of the wing locker to
allow it to mate with the leading edge and `fair into the area’ where the
seal will be installed.
REF. FIGURE 4
2)
Locate the Mylar of Detail 8 on the wing trailing edge upper surface. Notice the
outline of the Top Plate (85-3510-175) on the Mylar; position the Mylar to match
the previously installed Top Plate. Transfer the Locker Location Lines to the
wing surface to be used when locating the locker from side to side.
REF. FIGURE 6
3)
Tape one each 1/4 inch thick Aluminum Spacer (85-3510-125), concentric to
the pilot holes previously drilled for the locker attach holes, on to the Top
Plates (853510-175 and -177) at each wing locker aft attach position.
NOTE:
Placement of the 1/4 inch thick Aluminum Spacers in this step is a
starting point, additional adjustments may be required as the final
locker location is established
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
REF LOCATION ILLUSTRATION
4)
Place the Wing Locker (85-3550-5 left and -6 right) on top of the nacelle and
position as follows:
NOTE:
The appearance of the wing locker installation is determine by how
well it is located in these steps. Matching the contours of the wing
locker with the contours of the aft lower fairing is most important.
The locker sides may be trimmed and the fore and aft position
adjusted to suit the installation, provided the clearances in the following
steps are maintained.
a)
Push the locker forward until the locker bulkhead touches the nacelle bulkhead.
Check the inboard/outboard position of the locker by using the Locker Location
Lines from Step 2. Locker may be placed 1/2 inch inboard or outboard from
location lines.
b)
Mark the fore and aft location of the locker in relationship to the wing to
use as a reference point. Move the locker approximately 1" (one inch) aft
from this reference.
REF. FIGURE 5 AND 6.
5)
Temporarily reinstall the flaps but do not connect the actuator rod.
6)
Temporarily install Fairing Assembly (85-3550-013 left and -014 right) by
slipping the aft upper lip of the fairing over the flap trailing edge as shown. Trim
the forward edge of the fairing as required to clear the aft edge of the lower
nacelle. Tape the fairing in position on the flap.
7)
Check clearance between bottom of locker and wing structure and for proper fit of
fairing assembly as follows:
a)
With flaps in the down position, view the under side of the wing locker to
ensure that the bottom of the locker does not contact the upper wing
structure. The locker must rest on the mounting points and not on the wing
skin or structure. If clearance cannot be determined visually, remove the
wing locker and place soft putty on the two stiffener angles that run inboard
and outboard. Replace the locker, then remove and check the putty for
thickness, minimum gap must be 0.060 inch. Use Spacers (85-3510-125
and/or -157) to obtain desired clearance.
NOTE:
b)
The fuel vent tube location may be modified to prevent contact
with the wing locker.
Push the flaps into the up position and maintain enough pressure to simulate
flight loads. Check for a minimum gap of 0.10 inch between the flap upper
surface and the wing locker lower surface. Install more Spacers (85-3510125 and/or 157) if needed.
NOTE:
Revision M: November 1, 2017
The locker sides may be trimmed to allow the locker to nest closer
to the wing upper surface, provided the gap is maintained per Step
7a. The final trim of the locker sides is accomplished in a later
section.
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
REF. LOCATION ILLUSTRATION.
8)
The existing sixth and seventh screws of the nacelle fuel tank access panel
are used when installing the forward edge of the wing locker. The seventh
screws pickup the wing locker and the Upper Fairing (85-3510-173), the sixth
screws pickup the upper fairing and the existing nacelle. See Figure 7,
View M-M. Maintaining the locker position thus far established, determine the trim
line needed to pickup the seventh screw holes and trim the locker accordingly.
Be sure to maintain a good edge margin on the screws.
7.5 Aft Lower Nacelle Fairing Installation
REF FIGURE 5
1)
Remove the flaps from the airplane to accomplish the following steps.
2)
Position the aft lower nacelle fairing on the flap at the exact location marked
previously.
3)
Position the lower lip of the aft fairing forward bulkhead to eliminate gap between
bulkhead and fairing.
NOTE: If gap exists between the aft nacelle fairing and bulkhead, local shimming
may be required.
4)
Apply upward hand pressure to the flap until it stops to simulate in flight conditions,
measure gap between flap and locker. Maintain a .25-.30” gap while flap is being held
upward, trim locker as needed to achieve aforementioned gap. Reference Figure 1 Detail
A.
5)
Drill No. 30 holes in the forward edge of the aft fairing to match existing locations in
the bulkhead 27 places.
6)
Drill No. 30 holes in the aft edge of the aft fairing to match existing locations in the
flap trailing edge 27 places.
7)
Locate fastener holes in the outboard and inboard flanges of the fairing using the
dimensions shown in the figure. Drill No. 30 holes in the fairing and flap 30 places.
8)
Install the fairing with Blind Rivets (CR3212-4-2) 30 places (CR3212-4-3) 27 places
and with Rivet (MS20426AD4-5) 27 places.
9)
Locate two drain holes on center line of the fairing lower surface with one hole as
far forward as possible. Drill 3/8 holes as shown in figure.
10)
Fillet seal all edges of fairing using PR1422B2 sealant or equivalent.
Revision M: November 1, 2017
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
7.6 Aft Attach Structure Final Installation
1)
Position the wing locker in the exact location carefully marked in a previous section.
REF. FIGURE 4
2)
From inside the flap well, carefully run a No. 40 drill up through the existing locker
attach pilot holes and mark the bottom of the wing locker attach pads. Check to
see that hole will align with wing locker mounting pad. If hole location is acceptable,
drill a No. 40 pilot holes through the floor of the wing locker.
3)
4)
5)
6)
Remove the wing locker and enlarge aft attach holes in the wing skin, top plate,
backing plate and doubler to 0.250 inch diameter.
Locate Nutplate (MS21059L4 or optional NAS686A4) as shown in Details B and
C and Sections F-F and G-G. Drill No. 40 holes doubler, backing plate, skin, and
top plate 2 places each location. Countersink top plate 100 degrees to match
Rivet (MS20426AD3) 4 places.
Enlarge locker attach holes in locker and wing structure to 0.280 inch diameter.
Install nutplates with Rivet (MS20426AD3-10) 2 places each nutplate as shown.
7.7 Wing Locker Forward Attach Installation
REF. FIGURE 6
1)
Remove and discard the nacelle fuel tank access door attach screws 4 places as
shown.
2)
Reinstall wing locker in the same position as marked in a previous section.
Temporarily install the wing locker aft attach fasteners using Bolt (NAS1104-18 or
AN4-14A) with Washer (AN970-4).
3)
Position the forward portion of the wing locker so the gap between the wing locker
and wing skin is equal. Locate and drill 0.279 (+.012 or -.000) inch diameter holes
in the wing locker (only) to match the existing locations in the nacelle forward
access door 2 places. Countersink wing locker 100 degrees to match Washer (A3235028-24A).
REF. FIGURE 7
4)
Locate the Upper Fairing (85-3510-173) as shown in View M-M. Drill 0.279 (+.012
or -.000) inch diameter holes in the fairing to match the existing location in the
access door and countersink fairing 100 degrees to match. Screw (MS24694S49) 2 places. Drill No. 30 holes through fairing, nacelle access door, and nacelle
skin to match pilot holes in fairing 9 places. Additional fasteners in the upper
fairing will be located in a later step.
7.7.1 Inboard and Outboard Side Forward Fairing Installation
REF FIGURE 8
NOTE: Fairings will require some hand forming to fit the nacelle contour.
Study the over all layout and note trim points and dimensions before
cutting or trimming the fairings.
Revision M: November 1, 2017
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
1)
Document No. 87-1007
On the outboard side of the left nacelle, locate Fairing (85-3510-191). Trim fairing
as follows:
a)
Trim Fairings (85-3510-191) as required to match wing upper surface contour
and as required to obtain a clean transition with the -173 fairing at points A
and B.
b)
Trim Fairing (85-3510-191) as required to clear ice check light.
2)
Layout and drill 9 each 0.164 (+0.004 or -0.000) diameter holes in Fairing (853510-191).Locate holes as required to clear internal structure, maintaining a 0.32
minimum edge margin on the fairing.
3)
Layout and drill 1 each 0.164 (+0.004 or -0.000) diameter hole in Fairing (85-3510173). Locate hole as required to clear internal structure, maintaining a 0.32
minimum edge margin on the fairing.
4)
On the inboard side of the left nacelle, locate Fairing (85-3510-192). Trim to match
the upper wing surface contour and as required to obtain a clean transition with the
-173 fairing at points A and B.
5)
Layout and drill 9 each holes for CR 3242-4-2 Rivets through Fairing (85-3510192)
and structure using a No. 27 drill bit. Maintain a 0.25 inch minimum edge margin.
6)
Layout and drill 4 each 0.164 inch (+0.004 or -0.000) holes through Fairing (853510-192) and wing locker. Locate as required to clear internal structure. Maintain
a minimum edge margin of 0.32 inch.
7)
Layout and drill 1 each 0.164 inch (+0.004 or -0.000) hole through Fairing (853510192) and wing locker. Locate as required to clear internal structure. Maintain a
minimum edge margin of 0.32 inch.
REF. FIGURE 9
8)
On the outboard side of the right nacelle locate Fairing (85-3510-192). Trim fairing
as follows:
a)
Trim Fairings (85-3510-192) as required to match wing upper surface contour
and as required to obtain a clean transition with the -173 fairing at points A
and B.
b)
Trim Fairing (85-3510-192) as required to clear ice check light.
9)
Layout and drill 9 each 0.164 (+0.004 or -0.000) diameter holes in Fairing (853510-192).Locate holes as required to clear internal structure, maintaining a 0.32
minimum edge margin on the fairing.
10)
Layout and drill 1 each 0.164 (+0.004 or -0.000) diameter hole in Fairing (853510173). Locate hole as required to clear internal structure, maintaining a 0.32
minimum edge margin on the fairing.
11)
On the inboard side of the right nacelle, locate Fairing (85-3510-191). Trim to
match the upper wing surface contour and as required to obtain a clean transition
with the -173 fairing at points A and B.
Revision M: November 1, 2017
87-1007
Page 12
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Document No. 87-1007
12)
Layout and drill 9 each holes for CR 3242-4-2 Rivets through Fairing (85-3510191)
and structure using a No. 27 drill bit. Maintain a 0.25 inch minimum edge margin.
13)
Layout and drill 4 each 0.164 inch (+0.004 or -0.000) holes through Fairing (853510-192) and wing locker. Locate as required to clear internal structure. Maintain
a minimum edge margin of 0.32 inch.
14)
Layout and drill 1 each 0.164 inch (+0.004 or -0.000) hole through Fairing (853510192) and wing locker. Locate as required to clear internal structure. Maintain a
minimum edge margin of 0.32 inch.
7.7.2 Final Forward Fairing Installation
REF. FIGURE 7
1)
Remove left and right lockers.
2)
Enlarge holes in the nacelle for fairing attachment as shown in Detail N, 9 places for each
outboard fairing, 4 places for each inboard side fairing, 1 place at the inboard end of each
fairing and 1 place at the outboard end of each upper fairing. Install Rivnut
(NAS1329A08K75) 15 places.
3)
Remove the nacelle fuel tank access door. Install upper Fairing (85-2510-173)
forward edge with Rivet (MS20426AD4-4) 9 places. Install access door and install
Screw (MS24694-S49) through the fairing 2 places.
REF. FIGURE 8 & 9
4)
Install Fairings (85-3510-191 & 192) on the inboard side of the left and right nacelle
using Rivet (CR3242-4-2) 9 places for each fairing.
7.7.3 Final Installation
REF. FIGURE 6
1)
Place the wing lockers in position. Scribe and trim to provide a 1/4 inch gap between
the wing locker sides and the wing upper surface. This trim provides for the proper
fitting of Seal S-3760.
NOTE: The seal does not extend aft past the flap cove skin, so trim the locker
sides accordingly so they will fair with the flaps.
2)
Install Seal (S-3760 or OPTIONAL 85-3570) with PROSEAL 890 or PR1422 as shown in
View H-H. Drill (1) hole through seal and locker approximately 1/2 inch from forward edge
of seal and install (1) Screw (NAS525-832R7) and (1) Nut (MS20364-832) at each seal.
Ref. view A. Tighten nuts without distorting seals.
3)
Locate the Rubber Spacers (85-3510-131) on the wing skin as shown. Bond one spacer
at each location to the wing skin using Contact Cement (3M 1300L) 6 places. These
spacers protect the wing surface in the event that the wing locker tray bottom gives way.
4)
Install Wing Locker (85-3550-5 left and -6 right) with Bolt (NAS1104-18 or AN414A) and Washer (AN970-4) at the aft holes 2 places.
Revision M: November 1, 2017
87-1007
Page 13
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
5)
Document No. 87-1007
Install wing locker leading edge with Screw (MS24694-S49) and Countersink
Washer (A3235-28-24A) 2 places for each locker.
REF. FIGURE 8 & 9
6)
Install Fairings (85-3510-191 & 192) on the outboard side of the left and right nacelle
using Screw (AN525-8328R8 or MS35206-245) 9 places for each fairing.
7)
Install Screw (AN525-8328R8 or MS35206-245) in each end of Fairing (85-3510173) on both lockers.
8)
On each locker, install Screw (AN525-8328R8 or MS35206-245) 4 places on each
inboard fairing.
7.7.4 Final Flap Installation
1)
Install the left and right flap (Ref. Beechcraft Super King Air Maintenance Manual
Subject 27-50-00).
2)
3)
Carefully retract the flaps.
Trim the aft edge of the nacelle skin and/or the forward edge of the aft nacelle
fairing, if required to obtain 0.06 inch minimum gap between fairing and nacelle in
all flap positions.
8 Paint Preparation
The wing lockers are treated with an anti-static coating for dissipation of static precipitation
and covered with primer. To ensure good adhesion for the customer's finish paint the
installer should avoid automotive primer and filler systems. Apply customer's top coat
following the paint manufacturer's recommendations.
1)
Mask off area to be painted with vinyl tape.
2)
If surface is dirty, clean as follows:
a)
b)
Scrub surface with bristle brush and Bon Ami with water.
Wet sand lightly and wash with Trichloroethane (METHYL CHLOROFORM).
3)
If required, apply one coat of Class I Primer (MIL-PRF-23377), Urethane Compatible
Primer Yellow Base Desoto (#513 X 329), or equivalent.
4)
If application of primer is not required, recondition primer by sanding and a solvent
wipe with Methyl Chloroform or MEK.
5)
The following is offered as a dry tape test to check paint adherence after 24 hours at
room temperature cure.
a)
b)
3)
Apply one inch wide strip of Tape (3M250).
Press down firmly with burnisher or stiff putty knife, making sure there are
no bubbles.
c)
Remove the tape with one abrupt jerk; paint should remain on the surface.
Apply the first top coat (customers finish) of Polyurethane or Epoxy Enamel within
48 hours of primer application or primer reconditioning.
Revision M: November 1, 2017
87-1007
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BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
4)
Document No. 87-1007
Two coats of Polyurethane or Epoxy Enamel are required. Apply second coat per
paint manufacturer’s recommendations.
8.1 Anti-Static Treatment
This section provides instructions for the application of the anti-static coating, in case the
airplane will require repainting at a later date. This treatment is the recommended method
for dissipation of static precipitation. Use one of the following anti-static coatings or an
equivalent product.
Bostik West, Division of USN Corporation
Base 463-6-14 Activator CA-97
DeSoto Chemical Coatings
Base 528-302 Activator 910-006
Base 528-305 Activator 910-464
Tempo Paint and Varnish Company
Base 528-302 Catalyst 1980-CAS-5A
1)
Mask off area to be treated with vinyl tape.
2)
Strip primer with Fiber Resin ES-1. Optional: Remove primer by wet sanding. Sand only
until outer layer of resin is lightly abraded over entire surface.
CAUTION: FILLER SHOULD BE USED ONLY TO FILL MINUTE SURFACE
DEFECTS. L A R G E A R E A S O F F I L L E R M A T E R I A L A R E
D E T R I M E N T A L T O SUBSEQUENT PAINT ADHESION.
3)
If required, fill any pinholes using a static conditioner (Magna 28-C-1 or equivalent) filler.
Use hand pressure to force conditioner into pinholes.
4)
If required, apply surfacer (Laminar X-500, Epocast 156, or equivalent) to fill surface pits
and minor depressions. Use only when these conditions exist.
5)
Sand surface lightly and clean with naphtha-wet cheesecloth and wipe dry.
6)
Mix the anti-static coating material per manufacturers instructions.
7)
Apply coating to a thickness of 0.0004 to 0.0008 inch.
8)
Cure anti-static coatings at desired temperature per Table.
Revision M: November 1, 2017
87-1007
Page 15
BEECHCRAFT Super King AIR
200/200C/200T/A200/A200CT/B200/B200C/B200T/
B200CT/B200GT/B200CGT
• Nacelle Wing Lockers
Time Between
Application and
Raised Temp.
Temp °F
Document No. 87-1007
Time at
Cure Temp.
(Minutes)
Cool
Time
(Minutes)
Total
Time
(Minutes)
15
15
15
15
210-161
160-131
130-111
110-91
15
30
45
75
15
15
15
15
45
60
75
105
15
90-70
105
15
135
9)
Place two one inch wide and ten inch long strips of 3M conductive adhesive tape (Copper
X-1 181 or Aluminum X-1 170) 1 inch apart and parallel to each other on the cured antistatic surface. Press strips firmly against the surface.
10)
With a multimeter measure the resistance between the two metal strips. Multiply the
ohms reading by 10 to give resistance per square inch. If resistance per square inch is
more than 500,000 ohms, apply another coat of anti-static coating after sanding with 240
grit of finer abrasive paper and cleaning with naphtha-wet cheesecloth and wiping dry.
11)
Repeat resistance measurement per Steps 9) and 10).
12)
Within 24 hours after the application of the anti-static coating, wipe surface with naphthamoistened cheesecloth and apply one coat of Class I Primer (MIL-PRF-23377), Urethane
Compatible Primer Yellow Base Desoto (# 513 X 329), or equivalent.
9 RETURN AIRCRAFT TO SERVICE
1)
Make appropriate entry in the Aircraft Log Book.
Example: Installed Nacelle Stowage Lockers, Kit Number 87-1001-1 per STC
SA3857NM
2)
Complete three (3) copies of FAA Form 337, using the same entry as Aircraft Log Book.
Insert original in Aircraft Flight Manual, mail one (1) copy to local FAA GADO Office, and
retain one (1) copy for the installer’s records.
3)
Revise weight and balance data in Aircraft Flight Manual.
Add:
Raisbeck Nacelle Stowage Lockers
ARM
217.0
4)
WEIGHT
+97 pounds
MOMENT
21,049 pound inches
Complete Installation Record Form 145-() included in data package and mail to:
Raisbeck Engineering, Inc.
4411 South Ryan Way
Seattle, Washington 98178
Revision M: November 1, 2017
87-1007
Page 16