CESSNA AIRCRAFT
COMPANY
SINGLE ENGINE
STRUCTURAL REPA
IR MANUAL
Table 2. Approved Fastener Substitutions (continued)
Fastener
Collar
DIAMETER Fastener
Collar
REPLACE
WITH
(Refer to Notes 1,
5)
NAS7034 NAS1080K
(Refer to Notes 1,
6)
NAS464 (Refer to Note 8)
(Refer to Notes 1,
6)
NAS1103-
NAS1106
(Refer to Note 8)
(Refer to Notes 1,
6)
NAS1303-
NAS1306
(Refer to Note 8)
(Refer to Notes 1,
6)
NAS6203-
NAS6206
(Refer to Note 8)
(Refer to No
tes 1,
6)
NAS6603-
NAS6606
(Refer to No
te 8)
NOTE 1: Refer to ap
propriate tables for nominal diameters available.
NOTE 2: Available in oversize for repair of elongated holes. Ream holes to provide a 0.001 inch interference
fit.
NOTE 3: NAS529-4 thru -12 take NAS528 same dash number. NAS529-14 thru -20 take NAS179.
NOTE 4: Steel shank fastener designated for drive-on collars. Choose protruding head only.
NOTE 5: Steel shan
k fastener designated for squeeze-on collars. Installation requires sufficient space for the
tool and extended shank of the fastener. Choose protruding head only.
NOTE 6: Threaded f
astener.
NOTE 7: Preferred substitute fastener.
NOTE 8: When you substitute a threaded fastener for a high strength steel shank rivet, use one of these steel
nuts: AN365/MS20365, MS17825, MS21044, MS21045, MS51943 or NAS1079. Approval of the
use of the
se nuts in this application does not constitute a general approval to use these nut on high
strength bolts.
NOTE 9: GENERAL N
OTE: These fastener substitutions address shear strength and hole tolerances only. The
specific application may not allow all of these substitutions because of space considerations.
B. The United States Department of Defense no longer maintains MS and NAS standards. Identical
parts may
have MS, NASM or AIA/NAS part numbers.
EXAMPLE: MS20470AD4-6 rivets may also be identified as NASM20470AD4-6. NAS1738M4-4
rivets m
ay be identified as AIA/NAS1738M4-4.
C. Installation of Solid Shank Rivets.
(1) A large percentage of riveting of airplane structure is accomplished on thin gauge aluminum alloy,
and the w
ork must be accomplished without distorting or damaging the material with hammer
blows or riveting tools. All airplane power riveting is accomplished by upsetting the rivets against
a bucking bar instead of striking the shank with a hammer. To prevent deforming the rivet head,
a rivet s
et must be selected to fit each type of rivet. The depth of this set must not touch material
being riveted. Parts requiring heat treatment should be heat treated before riveting, since heat
51-40-00 Page 5
© Cessna Aircraft Company Jun 1/2005
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