Boeing Fasteners

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Boeing Fasteners

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AlTEON
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- INTRODUCTION TO FASTENERS
Introduction to Fasteners
This section provides a review of the most common
fasteners and auxiLiary parts used in Boeing airpLanes
today.
It shouLd be noted that the Latest revision of the
StructuraL Repair ManuaL or manufacturers'
documentation, shouLd be consuLted to ensure that this
information has not been superseded by design changes
or reguLatory authority action <F.A.A, D.O.T., C.A.A.,
etc. ).
Fastener Part Numbers

code in the hoLe Location cross in accordance with an
NAS 523 PLus SymboL System.
The fastener is identified by a two or three-Letter
code pLaced in the upper Left corner of the pLus
symboL. The code aLso defines the mating component,
where appLicabLe. Fastener diameter and manufactured
head Location are identified by the numeric-Letter code
pLaced in the upper right corner of the pLus symboL.
The diameter is given 1/32 NDS of an inch for aLL
permanant fasteners. ALL removabLe boLts are given in
1/16 TH of an inch. Countersinking and dimpLing
instructions are shown in the Lower Left corner of the
pLus symboL. The Lower right corner gives the grip
Length in 1/16TH of an inch.

To faciLitate standardization and usage, aLL vendor
fasteners and attachment devices are assigned a Boeing
part number. CLassifying part number prefixes used at
Boeing are:
BACB30
BoLts, LockboLts or Hi Loks
BACC30
CoLLar
BACF FiLLer
BACN10
Nuts and NutpLates
BACR15
Rivets
BACS
Shims or Screw
BACW
Washers
Fastener SymboLs
Permanent fasteners are identified on an engineering
drawing by pLacing the appropriate fastener symboL and

63-05-00
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AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL

FASTENER SYMBOL CODE
INSTALLATION: STD PER BAC 5004, FLUID TIGHT PER BAC 5047, TAPER SHANK PER BAC 5054
TAPER SHANK BOLT INFO

~

~

BASIC CODE
ENCLOSED = FLU~ "XX
OPEN = STANDARD
~
XX

I'

/
X X
X W

~DXC

MFDN =HDNEARLOC SIDE
F = FAR SIDE

" "~ SPOT WELD OPT

DIMPLE CSK INFO
o = DIMPLE
X = NUMBER OF SHEETS DIMPLED
C = CSK IN STRUCTURE

XZK-6

/

DIA DASH NO.

~ LENGTH

DASH NO.

= BACR15BB-6D

PROTRUDING HEAD
TYPICAL DRAWING
DETAIL SHOWING
FASTENER CALLOUT

= BACB30MY8C

PROTRUDING SHEAR
HEAD HILOK
(HEAD ON FAR SIDE)
8 UP 100'x.llR
GHl IHL

INTRODUCTION TO FASTENERS (SHEET 1)

FASTENERS - INTRODUCTION TO FASTENERS

63-05-00
-

1~4

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HEAD
TYPE

STEEL

A286

TITANIUM

CAD PLATED
(Low Alloy Steel 4340)

CAD PLATED
(Stainless Steel)

ALUMINIZED PAINT
(6AL- 4V)

STD
SHEAR HD

¢
Ltd

TENSION HD
I

SHEAR HD

Ltr

TENSION HD

.
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9o

Ltd

777 TRAINING MANUAL

1/64 OS 1/32 OS

STD

1/64 OS 1/32 OS

STD

1/64 OS 1/32 OS

BACC30M

BACC30M

BACC30R

BACC30M

BACC30M

BACC30R

BACC30M

BACC30M

BACC30R

XDA

XDE

XKA

XNL

XNP

XSG

YJA

YLE

YLF

BACB30FN

BACB30FQ

BACB30KF

BACB30FN*A

BACB30FQ*A

BACB30KF*A

BACB30NW*K

BACB30NW*K*

BACB30NW*K*

BACC30X

BACC30X

BACC30AC

BACC30X

BACC30X

BACC30AC

BACC30X

BACC30X

BACC30AC

XNB

XMS

XSL

XXZ

XUD

XTX

YLR

YXN

YXP

BACB30JC

BACB30LX

BACB30LY

BACB30JC*A

BACB30LX*A

BACB30LY*A

BACB30NY*K

BACB30NY*K*

BACB30NY*K*

BACC30M

BACC30M

BACC30R

BACC30M

BACC30M

BACC30R

BACC30M

BACC30M

BACC30R

XCZ

XDD

XKJ

XNJ

XNN

XSJ

YHY

YLC

YLD

BACB30FM

BACB30FP

BACB30KK

BACB30FM*A

BACB30FP*A

BACB30KK*A

BACB30MY*K

BACB30MY*K*

BACB30MY*K*

BACC30X

BACC30X

BACC30AC

BACC30X

BACC30X

BACC30AC

BACC30X

BACC30X

BACC30AC

XMX

XMY

XSM

XPB

XTZ

XUB

YLK

YLG

YLH

BACB30MB

BACB30MC

BACB30MD

BACB30MB*A

BACB30MC*A

BACB30MD*A

BACB30NX*K

BACB30NX*K*

BACB30NX*K*

SAMPLE HI-LOK DRAWING CODES

~

9

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FASTENERS - INTRODUCTION TO FASTENERS

63-05-00
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AlTEDN
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777 TRAINING MANUAL
FASTENERS -- PERMANENT AND REMOVABLE
THIS PAGE INTENTIONALLY LEFT BLANK

63-05-00
- 136 ALTEON PROPRIETARY - Copyright {el - See title page f o r ' s

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- PERMANENT AND REMOVABLE
Fasteners
There are two major classifications of fasteners;
permanent and removal. Permanent fasteners are those
that require destroying part or all of the fastener
when removing it from the airplane. Examples of these
are rivets, lockbolts or Hi-loks. Removable fasteners
would include fatigue or structural bolts.

63-05-00
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AlTEDN
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777 TRAINING MANUAL

BACR15BA
RIVET
BACB30FM
HEX-DRIVE OR HI-LOK

BACR15BB
RIVET

BACB30DX
LOCKBOLT

I

MS 90353
PULL RIVET

PERMANENT FASTENERS

BACN10HR
12 PT. NUT
BACN10JC
SELF LOCKING NUT

BACB30PC
SHOULDER BOLT
\

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>

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on

N

%
o

BACS21AE
QUICK-RELEASE SCREW

BACB30US
12 PT. TENSION BOLT
REMOVABLE FASTENERS

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'"

FASTENERS-PERMANENT AND REMOVABLE

63-05-00
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'.S

AlTEDN
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Telescoping bolt
where length is
uncertain

777 TRAINING MANUAL

For all tapered holes
(special nut required)

For out-ofround holes

For holes with
countersink on
wrong side

For mismatched
bolt holes

r

For holes too
near the edge

1J
~

For double countersunk holes

For redrilled holes
that still don't
match

For holes countersunk too deep

For holes not
square

For holes drilled
crooked and then
straightened up
(nut is hard starting)
Binocular bolt,
for double-drilled
holes

For use where pilot
hole does not clean up

Serrated head for
all vice-grip
torquing

Assembler's special,
for oversize and
stepped holes

SPECIAL FASTENERS
FOR THAT UNIQUE REPAIR

FASTENERS-PERMANENT AND REMOVABLE

63-05-00
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AlTEON
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777 TRAINING MANUAL
FASTENERS -- RIVETS - IDENTIFICATION MARKS
SoLid Shank Rivet MateriaLs

Solid Shank Rivet Head Styles

SoLid shank rivets are avaiLabLe in a variety of
materiaLs. The soLid shank rivets instaLLed on Boeing
aircraft are usuaLLy made from 2017, 2117, 2024 or 7050
aLuminum aLLoy. The part number suffix and rivet
identification marks give the rivet material.

Rivet head styles incLude universal and flush
varieties. FLush heads styles include standard, briLes,
shear, and index.

Rivets made from 2017, 2117, and 7050 aluminum alloy
and nickeL-copper alloy can be used and stored at room
temperature.
Rivets made from 2024 aluminum aLloy must be soLution
heat treated and then stored at a temperature of -10°F
(- 23°C), or lower. After removal from cold storage the
rivets must be completely driven within 15 minutes.
Rivets that are removed from coLd storage and not
instaLled should be discarded.
In some locations Monel rivets are used. Monel rivets
are made of 66% Nickel, 30% Copper and 4% Iron. Monel
is corrosion resistant and can be used in high
temperature appLications without significant property
reductions.

The modified fLush head is the briles rivet and gives
improved bearing in thin sheets, seals in the
countersink, improves fatigue Life, has greater head
strength in tension and can save weight due to improved
fatigue life in thin sheet.
7050-T73 rivets or briLes were introduced with the 767
program. These rivets have the same aLlowables as the
2024-T31 rivets but are sufficiently ductiLe that they
can be driven in the "as received" condition up to 1/4
inch diameter without cracking.
The modified universaL head and shear head offer a
weight savings over the standard universaL head or
flush, respectively.
The sLug rivet has no manufactured head, the head is
formed during driving, nearly always on automatic
drivers (Gemcor Drivematic).

o Other rivet aLloys include A286 CRES, 300 series CRES
~ and a Limited number of titanium-columbium are used in
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specific applications.

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63-05-00
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s

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL

MODIFIED
0
100 0
RIVET DESCRIPTION UNIVERSAL UNIVERSAL 100 CSK )HEAR HEAD
MATERIAL

2117(AD)

MARKS

2017(D)

RAISED DOT
EXCEPT [*]

2024(DD)

RAISED DOUBLE
DASH EXCEPT [*]

5056<B)

RAISED CROSS

1100(A)

82 CSK
INDEX
0

120 0
CSKiCB
BRILES

SLUG

STANDARD RIVET NO.
BACR15BB BACR15FT BACR15BA BACR15CE BACR15DG BACR15FH BACR15FV BACR15BO

8 a'i a'i ~
8 a'i a'i rY
E) Q'i
~
® ~'i
~
0 a'i
C)V
@
©'i ~
0
DIMPLED

82 CSK
INDEX
0

~ @/ (S:9
Ij?

i?

* NO HARKING

* NO MARKING

* INDENTED

~ (!j? ~
~

DOUBLE

D~

~

PLAIN

7050(KE)

RAISED CIRCLE
EXCEPT [*]

MONEL<M)
NICKELCOPPER

PLAIN

~
Ij?

* INDENTED

~ ~

* INDENTED

C~

FASTENERS - RIVETS - IDENTIFICATION MARKS

63-05-00
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AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- RIVET ALLOYS
Rivet Alloys
Rivet alloys in common use with their respective shear
strengths and material codes, are shown in the table.
Here are the applications for the different rivet
alloys:
1100-F Non-structural
5056-H32 For magnesium structure
2117-T3 General structure, nutplate attachment,
fuel-tight, and fatigue-critical joints.
2017-T3 General structure, fatigue-critical
joints, and not for use in fuel-tight joints.
2024-T31 Ice-Box, must be refrigerated after heattreat until installed. Used on the wings. Do not
use for nutplate attachment.
7050-T73 Use only where high strength is required.
Monel Use in titanium, CRES, and nickel alloy
structure. Requires high squeeze force.

63-05-00
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AlTEON
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777 TRAINING MANUAL
RATED SHEAR STRENGTH (Fsu)

ALLOY

RIVET MATERIAL CODE

9500 PSI

A

5056-H32 MAG USE ONLY

28,000 PSI

B

2117-T3 PRIMARILY WING

30,000 PSI

AD

2017-T3

38,000 PSI

D

2024-T31 ICE BOX RIVET

41,000 PSI

DD

7050-T73 (BRILES)

41,000 PSI

KE

MONEL

49,000 PSI

M

A286

90,000 PSI

C

1100F - NON-STRUCTURAL

<r-------'-q};----i
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I

XZK-6 = BACR15BB6D

p

I

Fast.
Shear

N

o

o
~

~
o

2

Example of Shear Strength Usage

~

P
= F\ X 4
= 1050 LBS
Fast.
3 *
Shear
~
38,000 psi

* NOTE: USE FRACTIONAL VALUES FOR ALL JOINT CALCULATIONS INVOLVING SHANK DIAMETERS
FASTENERS - RIVET ALLOYS

63-05-00
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AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- HEX-DRIVE, LOCKBOLTS AND RADIUS LEAD-IN BOLTS
Hex-Drive BoLts
Hex-drive boLts (Hi-Loks) have externaLly threaded pins
with no wrenching feature on the head. There is a
hexagon recess in the threaded end to prevent the pin
from rotating during instaLLation. The coLLar is
internaL threaded and seLf-Locking. The instaLLation
force is controlLed by a groove in the collar, which
shears off during installation.
SpeciaL power tooLs are often used for hex-drive bolt
instalLation. A hex key and standard wrench can aLso be
used for manuaL instaLLation.
Hex-drives are used when: soLid rivets do not have
sufficient shear strength, joint cLamp-up is necessary
or collar rotation provides manufacturing advantage.
Hexagon or twelve point seLf-Locking nuts may be
instaLled instead of hex-drive coLLars when: there is
not enough cLearance for colLar instaLlation, the use
of seal nuts is necessary or re-torque is necessary due
to seaLant squeeze out.
Lockbolts

g
~

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....
Q

The LockboLt pin has paralleL grooves instead of
threads with no wrenching features on the head. The
coLlar has a smooth cyLindricaL bore that is swaged
into the grooves of the pin.

pneumatic puLLing gun, which puLLs the shank of the
bolt through the hole and simultaneously swages a
collar into the pin grooves. The pin-tail breaks off at
a predetermined Load.
The stump type LockboLt is driven with a conventionaL
riveting gun, fitted with a lockbolt die set, and a
bucking bar.
NOTE: When a stump type is required and onLy the
corresponding puLL type is avaiLabLe, the pintail may be removed and fastener gun driven.
LockboLts are used when: soLid rivets do not have
sufficient shear strength, joint cLamp-up is necessary
or instalLation speed provides manufacturing advantage.
Lockbolt instalLation is fast and easy, but requires
open access to the parts. Where access is limited,
other fastener types are used.
Radius Lead-In BoLts
Titanium radius lead-in boLts are used for their good
fatigue properties in aluminum alloys. These fasteners
have a shank diameter that is 0.006 inches Larger than
the diameter of the hoLe in which they are to be
instaLLed, to provide a interference fit. There are two
oversizes availabLe for each nominaL size, for use in
repair work.

There are two types of lockbolts: pull and stump. The
pull type lockboLt is instalLed with a special

63-05-00
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AlTEON
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777 TRAINING MANUAL
COLLAR

STEP 1
HEX-DRIVE PIN IS INSERTED
IN THE HOLE AND THE COLLAR
IS MANUALLY THREADED ON
TO THE PIN.
SERRATED
STEM
TOOL\

1-.-__

9,

1---r=J

BREAK
. - NECK

STEP 2
POWER TOOL ENGAGES COLLAR.
ALLEN KEY ENGAGES THE END
OF THE PIN TO PREVENT
ROTATION OF THE PIN.

STEP 1

STEP 2

STEP 3

STEP 4

CHUCK JAW
PULLER

-~-~

STEP 3
THE FRANGIBLE NUT OF THE
COLLAR IS TWISTED OFF AND
DISCARDED. INSTALLATION IS
COMPLETE.

\FRANGIBLE
NUT
NOTES:
SELECT CORRECT GRIP LENGTH
FASTENERS FOR COMPOSITES HAVE LOW
TORQUE GROOVE, LARGE FOOTPRINT PROTRUDING
HEADS, AND LARGER FLANGED COLLARS.
REMOVAL REQUIRES SPLITTING COLLAR, OR
UNTHREADING COLLAR WITH SPECIAL TOOL

I

_ _ FRANGIBLE
NUT

FINAL
INSTALLATION SEQUENCE
OF A PULL TYPE LOCKBOLT

FASTENERS - HEX-DRIVE, LOCKBOLTS AND RADIUS LEAD-IN BOLTS

63-05-00
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777 TRAINING MANUAL
FASTENERS -- TENSION AND SHEAR
General
The 'Shear' head fasteners are used in applications
where shear and not axial tension is the primary mode
of load transfer. The 'tension' head systems are for
shear applications where higher tensile pre-load and
axial tensile capability are required.
Tension protruding head fasteners have a larger
diameter heads and more threads of engagement into
their collars than shear fasteners.
Tension flush head fasteners have larger diameter heads
and deeper countersinks than shear flush fasteners. See
the SRM chapter 51 in the fastener section for head
dimensions.
Do not substitute shear nuts or collars for tension
nuts and collars. The shear nuts or collars do not have
the same diameter or number of threads of engagement.

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63-05-00
- 146 ALTEON PROPRIETARY - Copyright (c) - See title page for

"ls

AlTEON
A BOEING COMPANY

.

/

7

777 TRAINING MANUAL

~--'---1gtr-.------?
<'-------=tj=J-

--

p

SHEAR JOINT

TENSION - PROTRUDING HEAD

,--[\J

10

---

TENSION - PROTRUDING HEAD

SHEAR - PROTRUDING HEAD
TENSION - FLUSH HEAD

.-IVt-

1/\-'---

II
SHEAR - FLUSH HEAD

SHEAR - PROTRUDING HEAD
LOCKBOLTS

HI-LOKS

FASTENERS - TENSION AND SHEAR

63-05-00
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AlTEDN
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777 TRAINING MANUAL
FASTENERS -- BLIND
GeneraL
BLind boLts and rivets are permanent fastener that are
avaiLabLe in aLuminum, MoneL, aLLoy steeL and A286
CRES. The fasteners are muLtipLe piece and have the
advantage of being instaLLed from one side.

SpeciaL bLind boLts are used for composite assembLies.
AppLications of bLind boLts are for assembLy of
eLevators and rudders, and for some of the boLted
repairs of 777 empennage structuraL boxes.

BLind BoLts

Removing bLind boLts can be difficuLt. The drive screw
must be driLLed out. TooLs are avaiLabLe from the
fastener manufacturer to assist in bLind boLt removaL.

There are two types of bLind boLts:

BLind Rivets

Threaded
Pu LL.
The tooL that instaLLs the threaded type rivet TURNS
the core stem, whiLe reacting against the fastener
head. The bLind head then forms and the joint
components are drawn together. FinaLLy, the core stem
breaks away compLeting the instaLLation.
The tooL that instaLLs the puLL type PULLS the core
stem instead of turning the stem.
Since blind bolts are used for Limited far-side access,
the formed head is difficuLt or impossibLe to inspect.
Therefore, it is important to exactLy foLLow the BAC
5004-3 instaLLation procedures. These incLude:

BLind rivets are not the same as bLind boLts. BLind
rivets are Lower in strength and cannot be substituted
for bLind boLts.
They shouLd never be used in areas of tension Loading,
vibration or where the head is subjected to prying.
BLind rivets are poor in fatigue because they do not
fiLL the hoLe Like soLid rivets.
If bLind rivets are used in a repair, the repair is
considered time Limited or interim and shouLd be
inspected at frequent intervaLs for Looseness. The
repairs showing blind rivets in structuraL repair
manuaL have FAA approvaL provided the inspections are
accompLished at the intervaLs stated.

Correct hoLe size
Correct grip length and diameter bolt
Using correct tooLs and technique

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AlTEDN
777 TRAINING MANUAL

A BOEING COMPANY

c;

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BLIND BOLT INSTALLATION

....
co
~

co:

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NOTES: SELECT CORRECT GRIP LENGTH
INSPECTION OF FORMED HEAD REQUIRED

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REMOVAL REQUIRES DRILLING OUT
CENTER STEM (DRILL GUIDES AVAILABLE)

BLIND RIVETS
FASTENERS - BLIND

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777 TRAINING MANUAL
FASTENERS -- OVERSIZE FASTENERS
Genera l
Oversize fasteners are generally used in repair
applications to clean up damage to a hole and to
provide the same fastener fit as was provided in the
original design. Occasionally, oversize fasteners are
used to provide an alternate load path.
As a general rule, if original rivets are replaced by
hex-drives or lockbolts, a 1/32 oversize fastener is
used in the repair. If original hex-drives or lockbolts
are replaced with hex-drives or lockbolts, a minimum of
1/64 oversize fastener is used. If rivets are replaced
with rivets then the same diameter can generally be
used.
Briles Rivets
When Briles Rivets are replaced, the next larger
diameter should always be used. Briles rivets are
available in 1/32 diameter increments up to 5/16" (Ref
BAC R15FV Series). Oversizing of holes and counterbore
is required to fit the appropriate size rivet.
In the event that use of an oversize Briles Rivet would
result in a knife-edge condition on thin skin, the
countersink depth of the original rivet may be
maintained and the rivet shaved flush after
installation. In many cases it would probably be
preferable to replace the Briles rivet with an OVERSIZE
protruding head rivet.

63-05-00
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AlTEDN
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777 TRAINING MANUAL

I
A

-H

PART NUMBER

DESCRIPTION

A

0

H

TO

BACB30MY6K()

3/16 HEX DRIVE

.295-.315

.1885-.1895

.045-.055

.181-.184

BACB30MY6K()X

1/64 OVERSIZE

.295-.315

.2016-.2026

.045-.055

.181-.184

BACB30MY6K()Y

1/32 OVERSIZE

.295-.315

.2168-.2182

.045-.055

.181-.184

FACTORY FASTENER

REPAIR FASTENER TYPE

TYPICAL REPAIR FASTENER SIZE

RIVET

RIVET

SAME DIAMETER

RIVET

HEX-DRIVE OR LOCKBOLT

1/32 OVERSIZE

HEX-DRIVE OR LOCKBOLT

HEX-DRIVE OR LOCKBOLT

1/64 OVERSIZE

FASTENERS - OVERSIZE FASTENERS

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AlTEDN
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777 TRAINING MANUAL
FASTENERS -- REMOVABLE FASTENERS
Bolts

Tension and Shear Bolts

A bolt, generally, has a smooth cylindrical shank and
is intended to be installed by turning the mating nut.

Tension and shear-rated bolts may have hexagonal, 12
point, or countersunk heads with long threads for
tension joint installations, or short threads for shear
applications. Material options are the same as for
fatigue-rated bolts. Wherever possible, bolts should be
installed with the head uppermost or forward as
applicable, except as noted in relevant maintenance
documents or engineering drawings.

Removable bolts are used for the following conditions:
Permanent fasteners that require sufficient shear,
axial tension or fatigue performance
Joint clamp-up is necessary
Occasional disassembly is required

Bolt Threads
Removable bolts can be categorized as fatigue, tension,
or shear rated.
Fatigue-rated Bolts
Fatigue-rated bolts are used for high strength
applications in critical joints and have 12 point
protruding heads with long threads. They are available
in a tension strength range of 160 to 220 KSI, and are
typically made from Alloy Steel, A 286 (CRES), Inconel
718 and 6AL-4V Titanium. (Note: Because of stress
corrosion cracking problems, H-11 steel bolts
(BACB20MT) are no longer used for design or recommended
as replacement fasteners).

~

'"

All Boeing standard bolts have rolled threads after
heat treatment, not machined threads. Rolled threads
have a smooth uniform root radius which blends with the
thread flanks to provide improved fatigue life through
lower stress concentrations.

Countersunk washers should always be used under the
head of fatigue-rated bolts. Otherwise, the washer will
ride in the radius under the bolt head.

~

9[5
I

9
'"'"

63-05-00
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"ls

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL

SHORT THREADS\

SHORT THREADS \

~)-----~~
'

-E+-+ -

..

1~1t-

v
COUNTERSUNK
HEAD BOLT

r-

--+-+-

- ---

LONG THREAD (TENSION) BACB30LH
SHORT THREAD (SHEAR) BACB30LU

12 POINT HEAD BOLT LONG THREAD TENSION BACB30NJ
SHORT THREAD BACB30LT

LONG THREADS\

/r-

0

-

P\+TV

bL-

-

/

--

-+

-

/

"

~

-

/

-

'\.

f----

\.

0

"'-

'-------

<-

HEX HEAD BOLTS LONG THREAD (TENSION) BACB30NE
SHORT THREAD (SHEAR) BACB30NF

12 POINT HEAD FATIGUE TENSION BOLT
BACB30US

ALL "BAC" BOLTS ARE PURCHASED
WITH ROLLED THREADS

FASTENERS - REMOVABLE FASTENERS

63-05-00
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AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- BOLT STRENGTHS
Fastener Alloys
Mechanical fastener strength properties for the
fastener alloys summarized in the table are independent
of the materials in which they are installed, and apply
only when the fastened materials are sufficient in
strength and thickness to develop the full strength of
the fastener.
Boeing part standards should be referred to for
fastener dimensions, materials, finishes and
qualification requirements. For fastener installation
requirements, see the applicable Boeing process
specification.

63-05-00
- 154 ALTEON PROPRIETARY - Copyright

(c) -

See title page for

'.5

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL

MINIMUM RATED STRENGTH - ksi

ALLOYS

SHEAR (Fsu)

TENSION

(F tu)

STEEL
8740/4340

95

160

CL>

125

220

95/110

160/200

PH 13-8 MO

125

220

INCONEL 718

125

220

95

160

H-11
CRES
A286

TITANIUM
6AL-4V

Q

Q

~
N

.:
'"
Q

%

$

CL>

H-11 IS NOT RECOMMENDED DUE TO STRESS CORROSION SUSCEPTIBILITY

~

FASTENERS - BOLT STRENGTHS

63-05-00
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AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- BOLT TORQUE REQUIREMENTS
Bolt Torque Requirements
Pre loaded bolts improve both the fatigue resistance and
the locking characteristics of the nut and bolt
installation. They also introduce a beneficial
compressive stress around the rim of the hole which
counteracts the tendency for stress concentration
cracks to occur at the edge of the hole caused by
applying a shear load to an unpreloaded bolt.

Re-application of torque to removable bolts is
recommended if the joint uses faying surface sealant in
any interface. Fay surface sealant may squeeze out of
the joint when bolts are tightened, resulting in
partial loss of bolt preload, unless torque is then reapplied to the fastener. It is important that torque
application be completed within 60 minutes of the
squeeze-out life remaining in the fay surface and
fastener sealant.

It is important that the maximum allowable torque value
is not exceeded as torque values are based on the proof
load for the fastener material which is approximately
equivalent to the yield strength.
For CRES steel nuts, use torque values given for shear
type nuts.
Use BAC (Boeing Airplane Company) standard torque
tables as a guide whenever specific torque values are
not called out on the engineering drawing or in
approved maintenance documents such as the structural
repair or maintenance manuals. Torque wrenches should
be used when engineering drawings or maintenance
documents indicate that specific torque values are to
g be applied.
~

~

In cases where space ;s limited, the head end of the
~ bolt instead of the nut, may need to be rotated to
~

'"

~
88,

,
9
'"'"

obtain the necessary torque. When the fastener head is
used for this purpose, the high side of the torque
range should b e use d .

63-05-00
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ls

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
1I1111NII 7 . 7
757-200
STRUCTURAL REPAIR MANUAL
NUT
PART
NO.
BOLT
PART
NO.

I B/
./

,

FASTENER
DIAMETER
AND
THREAD
SIZE

I

A/'

:~SING

ADAPTER IN LINE
WITH WRENCH. CORRECTION
REQUIRED
T1 - T x A

- A+ B

T
T1

= ACTUAL
= TORQUE

TORQUE ON NUT
WRENCH READING

BACN10GW, BACN10JA, BACN10B,
BACN10JB, BACN10RM,NAS577,
BACN10JD,(7/16 THRU 1-1/4 ONLY),
NAS1805
BACB30NG, BACB30NH, BACB30MT,
BACB30FD, BACB30MR, BACB30L~~.
BACB30PN, BACB30NE, BACB30LM,
BACB30US
BACB30NM, BACB30LN, BACB30NS,
BACB30EM, BACB30LP, BACB30LU,
BACB30LR, BACB30MS, BACB30NN,
NAS6603 THRU NAS6620, NAS6703
THRU NAS6720
NUT TIGHTENING TORQUE RANGE (POUND-INCH)~

BACN10HR, BACN10JG, BACN10HC

DRY BOLT

0>

--10-32
1/4-28
90-125
180-250
5/16-24
3/8-24
300-500
7/16-20
510-840
1/2-20
870-1300
9/16-18
1300-1800
5/8-18
1900-2300
3/4-16
3300-4300
7/8-14
5100-6700
1-12 OR 1-14
7000-10,900
1-1/8-12
9500-13,000
15,800-19,200
1-1/4-12
1-3/8-12
20,000-24,000
--1-1/2-12
~MAXIMUM

DRY BOLT

LUBRICATED
BOLT

LUBRICATED
BOLT

0>

--70-80
145-180
275-330
370-440
500-575
800-1000
1350-1650
2800-3300
3900-4500
6200-7000
8300-9400
11,000-12,000
16,000-17,000

---

30-35
65-100
130-200
220-410
370-690
630-1070
1000-1470
1400-1900
2400-3500
3700-5500
5100-8900
6900-10,700
11,500-15,700

-----

20-25
50-75
90-125
150-250
260-425
440-650
700-920
1000-1200
1700-2150
2600-3400
3600-5500
4900-6700
7500-9700

-----

NUT TIGHTENING TORQUE VALUES
TORQUE + OR - 10 PERCENT WHEN BOLT IS INSTALLED BY WRENCHING HEAD.

SEE STRUCTURAL REPAIR MANUAL FOR LATEST DATA.

FASTENERS - BOLT TORQUE REQUIREMENTS

63-05-00
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AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- WASHERS
Washers
For general use, plain washers (AN 960, BACW10BP()P)
are used under nuts. They provide a uniform bearing
area and act as a spacer to adjust for fastener grip
length and material thickness. The bolt and nut
installation specification (BAC 5009), allows one
washer under the fastener head, and two washers under
the nut. Plain washers may also used under the collars
of lockbolts or hiloks or under the head of solid
rivets to distribute the fastener bearing load over a
larger area. This is particularly important in plastic
or carbon fiber assemblies. In installations where
spring lockwashers (AN 935) are used, plain washers
must be fitted between the part and the lockwasher to
prevent damage to the material.

Q

In fatigue critical joints, preloaded-indicating
washers are used to optimize fatigue life and handle
greater in-service stresses. They act by compressing
the inner ring to the point where the outer ring cannot
be moved, thus achieving the required preload.

Countersunk washers (BACW10BP()C) are used under the
head of protruding head bolts to provide head-to-shank
fillet relief on high strength fasteners such as
BACB30US and BACB30LE bolts. Self-aligning washers
(BACW10CA) are used with fasteners in non-parallel
joint design where counterboring of the slope surface
is unacceptable. These washers will accommodate a
maximum slope of 8 degrees. A concave and a convex
washer make up the self-aligning washer assembly.

Q

~

N

As an option to aluminum, plain cadmium plated steel
washers are frequently used adjacent to structural
~ surfaces as they better resist the cutting action of
co:
~ the nut, especially if a specified torque has to be
~ applied. Where the material next to the nut is steel,
use steel washers.
'"

r=;

*
~

63-05-00
- 158 ALTEON PROPRIETARY - Copyright (c) - See title page for

ts

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL

~A

-t- -{}A-A

CONVEX

L.A

COUNTERSUNK WASHER

GENERAL PURPOSE FOR WASHERS:
- DISTRIBUTION CLAMP UP BEARING LAOD
- PREVENT GALLING
- DISSIMILAR MATERIAL COMPATIBILITY
- GRIP LENGTH ADJUSTMENT
- FILLET RELIEF FOR FATIGUE RATED BOLTS
- SELF-ALIGNMENT FOR ANGLES BETWEEN 2-8 DEGREES

CONCAVE

SELF-ALIGNING WASHER
2 - 8 DEGREES

2 WASHERS

~ (WP22, BACW10AK)

TYPICAL INSTALLATION

OUTER PLI RING
OUTER
PLI RING

INNER PLI RING

-

~iiiiiijj

TOOL HOLES (3)
120· APART
(APPROXIMATE)

()

v

(BEFORE LOADING
CONDITION ILLUSTRATED)

BEFORE LOADING
NOTE: OUTER PLI RING
- - FREE TO TURN.

AFTER LOADING
NOTE: INNER PLI RING COMPRESSED,
OUTER PLI RING NO LONGER
FREE TO TURN; INDICATING
PROPER PRELOAD. INNER PLI
RING NOT REUSABLE.

PRELOAD INDICATING WASHER (PLI)
FOR 220 KSI NUTS BACW10AM

FASTENERS - WASHERS

63-05-00
- 159 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- NUTS / NUTPLATES
Nuts / Nutplates
Nuts are generaLLy classified as tension or shear.
Tension nuts are avaiLabLe in strengths of 180 or 220
KSI. Shear nuts are avaiLabLe in 125 KSI strength. Nuts
are seLected to have a tensile strength equaL to or
greater than the mating boLt or screw. Nut pLates are
used in "cLose outs" or other pLaces with Limited or no
access. They are attached with rivets. NutpLates are
primariLy used in shear appLications and are
predominantly of 125 KSI strength with a limited number
rated at 160 KSI.

ALignment of the casteLLated nut and the boLt cotter
pin hoLe whiLe staying within the specified torque
range is accompLished by changing the boLt grip Length
and/or adding washers.
For fLight safety appLications, FAR 25.607 states that
each removabLe boLt, screw, nut, pin or other removabLe
fastener must incorporate two Locking devices.

ALL removabLe fasteners require Locking mechanisms.
Some exampLes are:
SeLf-Locking nut
CastelLated nut secured with a cotter pin
Safety wire.
The threads on seLf-Locking nuts are typicaLLy deformed
to provide the additionaL friction to hold the
fastener. The minimum to maximum Locking torque range
is used to find the condition of a used seLf-Locking
nut and boLt set. See chapter 20 of the Maintenance
ManuaL (Standard Practices) or procurement
specification BPS-N-70 for these ranges.
CasteLLated nuts
fasteners having
'"
~ shalL be secured
8, the instaLLation
9
9 5018, MS33540 or
'"..,
~

are used with externalLy threaded
drilled holes in the threaded area and
with cotter pins in accordance with
requirements specified in BAC 500 9 ,
chapter 20 (Standard Practices).

63-05-00
- 160 ALTEON PROPRIETARY - Copyright (c) - See title page for

's

AITEON
A BOEING COMPANY

777 TRAINING MANUAL

SHEAR NUT
BACN10JC

TENSION NUT
BACN10HR

CLIP-ON

DEFORMABLE THREADS

BACN10KB

BACN10KF

BACN10KA

BACN10YD

NUTPLATES

FASTENERS - NUTS / NUTPLATES

63-05-00
- 161 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- SCREWS
Screws
Screws made of lower strength materials than bolts, are
used in non-structural applications such as in
passenger and flight deck areas, baggage compartment
sidewall liner attachments, fairings, removable panels
and other secondary structural installations.
Screws which have the same strength as bolts of the
same diameter, may be used for structural joints,
although it is important to ensure that screw threads
are not placed in bearing.
Screws are identified by several coding systems, of
which the most common are the 'AN' and 'NAS' series.
'AN' identifies the fastener as an Air Force/Navy
Standard and 'NAS' signifies that the fasteners are
National Aircraft Standards. Boeing numbers are used
for special purpose fasteners. An example of these
would be the BACS12ER titanium screws used in the flux
valve installation where a corrosion resistant, antimagnetic fastener is required. Another example is the
BACS12FA screw used to attach the sidewall liners in
the lower baggage compartments.

..
>

00

9
g
I

9
'"'"

63-05-00
- 162 AlTEON PROPRIETARY - Copyright (c) - See title page for

s

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL

BACS12FA

BACS12ER

-6--+-1NAS 623

15
o
~

,
....
o

.
>

'"
00

o
o
I
o

J:

$",

--1--

N

-

$

'"

I

NAS 517

-It
/"=-------t.

-

--

-.

--

.or: ------0

NAS 1801

9
'"

'"

FASTENERS - SCREWS

63-05-00
- 163 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- HOLE FIT CLASSIFICATION AND APPLICATION
General
The National Aircraft Standard 618 lists the industry
standards for bolt diameters and corresponding hole
sizes.
The fits for the various hole classifications have been
shown for several representative bolt sizes.
The hole tolerance limits for class II and class III
holes are not as critical as those for the other
classes.
Interference fit holes are always smaller than the
fastener shank diameter.
Clearance fit holes are always larger than the fastener
shank diameter.
Fit Classification
Transition fit holes can be smaller, same or larger
than the fastener shank diameter.
Close Ream holes are same or slightly larger than the
fastener shank diameter.

.

Class I, II and III holes are larger than the fastener
shank diameter.

>

""
I'-

N

'i'

9

9
'"'"

63-05-00
- 164 ALTEON PROPRIETARY - Copyright (c) - See title page f o r ' s

AlTEDN
A BOEING COMPANY

TRANSITION
SIZE

BOLT
DIAM

777 TRAINING MANUAL

II=>

CLOSE REAM

CLASS I

CLASS II

CLASS III

HOLE
DIAM

FIT

HOLE
DIAM

FIT

HOLE
DIAM

FIT

HOLE
DIAM

FIT

HOLE
DIAM

FIT

3/16

.1885
.1895
!:L:>

.190
.187

+.0015
-.0025

.1905
.1895

+.0020
+.000

.194
.190

+.0055
+.0005

.199
.190

+.0105
+.0005

.229
.218

+.0405
+.0285

114

.2485
.2495

.250
.247

+.0015
-.0025

.2505
.2495

+.0020
.000

.254
.250

+.0055
+.0005

.261
.250

+.0125
+.0005

.291
.279

+.0425
+.0295

II=> IN

ALUMINUM STRUCTURE ONLY

!:L:>SHOWN AS .190 IN SOME HANDBOOKS

HOLE
CLASS I FICA TION

.

FASTENER APPLICATION

TRANSITION FIT

LOCKBOLTS AND HILOKS IN ALUMINUM STRUCTURE

CLOSE REAM

LOCKBOLTS AND HILOKS OTHER THAN THE ABOVE.
CLOSE TOLERANCE BOLTS WITH <4 FASTENERS IN THE JOINT

CLASS I

STANDARD BOLTS AND CLOSE TOLERANCE BOLTS WITH 4 OR MORE
FASTENERS IN THE JOINT

CLASS II

BOLTS ATTACHING REMOVABLE PANELS

CLASS III

BOLTS ATTACHING REMOVABLE PANELS WHICH ARE NOT INTENDED TO PICK
UP ANY STRUCTURAL LOADS

>

'"
....
N

o

6

~

'i'

'"'"

FASTENERS - HOLE FIT CLASSIFICATION AND APPLICATION

63-05-00
- 165 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENER -- SUBSTITUTION
Genera l
When adapting the typical repairs shown in the SRM to
suit actual conditions, it may be necessary to use
fasteners of a different type to those originally
specified.

An ALERNATIVE fastener is a fastener with equal or
greater strength properties than the initial fastener.
However, an alternative fastener cannot be used when:
They do not give the necessary pressure or fuel
sea l
Non-magnetic fasteners are necessary and the
fastener is magnetic
Fastener thread length, grip length or diameter is
not available
Access does not permit fastener installation
Fastener installation tools are not available.

The fastener selection for SRM repairs is based on:
Strength
Corrosion protection
Weight
Temperature
Fatigue properties
Method of installation.
It can be necessary to install alternative fasteners
because:
The specific fastener is not available
It is not easy to get access to a necessary
location
The special repair is different from the general
repair.

~

'"

An EQUIVALENT fastener is a fastener which is directly
interchangeable with the initial fastener. Usually the
equivalent fasteners are given under a vender part
number and are not always the same as those supplied to
the Boeing Company.

NOTE: Do not use the Fastener Substitution Tables to
find alternatives for the fastener listed in the
ALTERNATIVE column.
Use of fasteners from different fastener groups is
permitted, but the alternative fasteners must have
equal or greater strength. Tension-type fasteners are
permitted in tension and shear applications. However,
shear-type fasteners are not permitted in tension
applications.
An example of a fastener substitution table is shown
below.

o
N

9o
~
9

'"'"

63-05-00
- 166 ALTEON PROPRIETARY - Copyright (c) - See title page for

ls

AITEDN
A BOEING COMPANY

777 TRAINING MANUAL

~

III'
fj7Qfj7

<f!!I

STRUCTURAL REPAIR

o not substitute cadmium plated fasteners
~ 0f or
bare or BMS 10-85 coated fasteners when

REPAIR FASTENER

OItJ6INAL OR SPECIFIED
CODE

PART NUI18ER

XCI

BACB30FMO-()

m

DESCRIPTIONI!I

[!]

AllO)' STEEL, CAD

PLATED, 95 I<SI SHEAR,
CETYL ALCOHOL lUBRi[ATED, 450°f MAXIMUM
TEMPERATURE

EQUIVALENT

'" "'*r

HI-SMEAR

HUBPS

::~:~~:=i ~;~:

SPS
VOl-SHAN

MUBPS
Nl18PS

BACB10fM()AK()
BACB1OMB()-()

OEUTSCH

HL18PS

BAtB1OM8( )A()

IIEST COAST Nl18PS
VEST COAST 11(22-

8,1.(830611( I-()
IIACB3061HlAO

HI-SHEAR

NUOVAP

HI-SHEAR
HI-SMEAR

H110VAZ

HI-SHEAR

HSTlOA6
HST10AP
HST10AZ

HI-SHEAR
HI-SHEAR
YHU

BACB10FHOk()

[!]

VHY

AllOY STEEL, BMS 10-85
COATED, 95 KSI SHEAR,
CETYL ALCOHOL LUSRICATED, 150°F MAXIMUM
TEMPERATURE

DEUTSCH

SPS
HI-SHEAR
VOl-SHAN
HI-SHEAR

BACBJOFMOA()

XNJ
Y6E

A286 CRES, CAl) PLATEI),
95 I(SI SHEAR, CETYL
ALCOHOL LUBRICATED,
450°F MAXIMUM
TEMPERATURE

HI-SHEAR
HI-SHEAR
HI-SHEAR
SPS
DEUTSCH
VOl-SHAN
WEST COAST
HI-SHEAR
HI-SHEAR
HI-SHEAR
WEST COAST

HL10VAP
HL10VAZ
HL440UC
HL440UC
HL440UC
HL440UC
Hl440UC
HSnOA6
HST10AP
HSnOAZ
wcno-

A286 CRES, BMS 10-85
COATED, 95KSI SHEAR,
CETYl ALCOHOL LUBUCATED, HooF MAXIMUM
TEMPERATURE

HI SHEAR
HI-SHEAR
HI-SHEAR
DEUTSCH
SPS
HI-SHEAR
VOl-SHAN
HI-SHEAR
Ill-SHEAR
HI-SHEAR

HL10VAP
H110VAZ
Hl440AP
Hl440AZ
HL440AZ
HL440AZ
HL440AZ
HST10A6
HST10AP
HsnOAZ

BACBJOFM()AK()

XTC

BACBJOMY()C{)[!J 6AL-4V TITANIUM, CAl)
PLATEO,95I(SI SHEAR,
CETYL ALCOHOL LUBRICATED, 450°F MAXIMUM
TEMPERATURE

BACBlODX()-()
BACB1ODX()A()
BACB1OHC()-()

Il!II!lI!l

...

[8J

[!J!)
ImJ

i nstalled through titanium structure.
0 o not substitute lockbolts for hex drive
b olts when installed through composite
S

tructure.

I!I!I
I!I!I
[!(!J

BA(830"(( IA()

::~:~~~~~:~~: }rnm
BACB10NE()-O
BACB30lH()-( )

I!I!l

'UO"} I!l :~~:~~:::!~:: }[!!I!J

MUIIKD

HI-SHEAR
HI-SHEAR
HI-SHEAR

YMY
YMS

XTJ
VAX

Hl44D

HL181(D
HL181(D
H110VA
H110VAZ
H5nOA6
HSnOAP
HST10AZ

HI-SHEAI!

'"

ALTERNATIVE

BACB1OLJ()-()

,,,",.NF()-()

BACB10FI)O-()
BACBJOFI)OPO
BACBJOVT()I«)
BACBJOVN()I«)

BOLT - HEX DR IVE - PROTRUD ING HEAD -

I

REPAIR FASTENER
ORIGINAL OR SPECIFIED
CODE
XCZ
YEF

YHU
YHY

PART NUMBER
BACB30FM()-()

BACB30FM( lK( l

DESCR IPTION

[!)

[!)

[!!]

EQUIVALENT

AL LOY STEEL, CAD
PL ATED, 95 KSI SHEAR,
CE TYL ALCOHOL LUBRICA TED, 4500F MAXIMUM
TE MPERATURE

AL LOY STEEL, BMS 10-85
CO ATED, 95 KSI SHEAR,
CE TYL ALCOHOL LUBRICATED, 3500F MAXIMUM
TE "PERATURE

SHEAR

TABLE V
XEK
XNJ
YGE

Fastener Substitution
F; gure 1 ( Sheet 11>

BACB30FM()A()

>

:.

51-30-03

Page 14
Mar 15/94

747 SRM

L----

FASTENER

A2 86 CRES, CAD PLATED,
95 KSI SHEAR, CETYL
AL COHOL LUBRICATED,
45 OoF MAXIMUM
TE MPERATURE

SPS
HI -SHEAR
SPS
VOl-SHAN
DEUTSCH
WEST COAST
WEST COAST
HI-SHEAR
HI-SHEAR
HI-SHEAR
HI-SHEAR
HI-SHEAR
HI-SHEAR

62550_}
HLl8PB
HLl8PB
HL18PB [!)
HLl8PB
HLl8PB
WC22HLIOVAP
HL10VAZ
HL440
HSTIOAG
HSTIOAP
HST10AZ

DEUTSCH
SPS
HI-SHEAR
VOl-SHAN
HI-SHEAR
HI-SHEAR
HI-SHEAR
HI-SHEAR
HI-SHEAR

~t~:~u I!J

HLl8KD
HL18KD
HL10V
HL 10VAZ
HSTIOAG
HSTIOAP
HSTI OAZ

HI-SHEAR
HI-SHEAR
HI-SHEAR
SPS
DEUTSCH

HLIOVAP
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63-05-00
- 167 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AITEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- FASTENER FINISH REQUIREMENTS
THIS PAGE INTENTIONALLY LEFT BLANK

63-05-00
- 168 ALTEON PROPRIETARY - Copyright

<c) - See title page f o r ' s

AITEDN
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- FASTENER FINISH REQUIREMENTS
Fastener Finish Requirements
The fastener finish requirements for use with various
aircraft materials are shown. These recommendations
should be followed so as to minimize the potential for
corrosion resulting from rework operations.
The recommended fasteners in aluminum structure are BMS
10-85 (aluminum-pigmented coating) coated titanium, BMS
10-85 coated A-286, or cadmium-plated A-286. Cadmiumplated alloy-steel fasteners are a structurally
satisfactory alternative. However, in a corrosive
environment the cadmium plating, which is a sacrificial
coating, may disappear allowing the alloy-steel
fastener to corrode. This may result in the ruststreaking of the surrounding structure and/or the start
of corrosion of any adjacent aluminum structure.
All steel and titanium fasteners must be installed wet
with BMS 5-95 or equivalent sealant.
With the exception of 5056 rivets installed in aluminum
structure, it is recommended that all rivets are
installed dry. Fay surface sealant does not need to be
removed from the fastener holes before rivet
installation. However, because of their head geometry.
Briles rivets (BACR15FV) should never be installed wet
with sealant, since the reduction in hole filling
ability wiLL degrade the fatigue quality of the joint.
See the StructuraL Repair Manual for the latest
information.

63-05-00
- 169 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL

FASTENER AND FASTENER HARDWARE INSTALLATION
DETERMINE THE METAL GROUP OF EACH ALLOY USED IN THE ASSEMBLY, THE LOCATION OF
EACH ALLOY AND THE LOCATION WITHIN THE AIRPLANE, THEN SELECT THE LOCATION WITHIN
THE AIRPLANE, THEN SELECT THE INSTALLATION PROTECTION FINISH CODE FROM TABLE.
METAL GROUP

. 0

LOCATION IN THE AIRPLANE
INT
FASTENER OR HARDWARE t
ALUMINUM
1
ALLOY STEEL, CAD PLATED
1a
X
CRES, PASSIVATED OR DRY FILM LUBED
CRES, CAD PLATED or BMS10-85 COATED 1a
X
TITANIUM
TITANIUM, BMS 10-85 COATED
1
X:
1:
2:

a:
b:
INT:
EXT:

IT]

IV
III
III
IV y,:
IV
/<
Xv
~
~
EXT INT EXT INT EXT INT EXT INT EXT INT EXT
II

1
X
X
2
X
2

2
1a
X
2
X
2

2
X
X
2
X
2

X
X
X
2b
X
2

X
X
X
2b
X
2

X
2
X
2
X
2

X
X
X
2
X
2

X
X
X
2b
X
2

X
X
X
2b
X
2

X
X
1
1b
1
1

X
X
1
1b
1
1

DO NOT USE
NO FINISH (DRY INSTALLATION)
FOR PERMANENTLY INSTALLED FASTENERS, WET INSTALL WITH BMS5-95 SEALANT.
FOR REMOVABLE BOLTS/NUT COMBINATIONS, INSTALL WITH BMS3-27.
FOR FASTENERS, INSTALLED INTO NUT PLATES, PRIME HOLE WITH BMS10-11 TYPE I PRIMER AND
INSTALL WIH MIL-C-11796, CLASS3.
FOR BLIND FASTENERS, WET INSTALL WITH BMS5-95
CADMIUM-PLATED FASTENERS AND FASTENER HARDWARE SHALL NOT BE USED IN CONTACT WITH
TITANIUM OR CFRP
INTERIOR (NOT EXPOSED TO OUTSIDE ENVIRONMENT)
EXTERIOR (EXPOSED TO OUTSIDE ENVIRONMENT)

[] METAL GROUP:
I
MAGNESIUM AND ITS ALLOYS
II CADMIUM-TITANIUM PLATE AND CADMIUM ZINC,ALUMINUM AND THEIR ALLOYS
III IRON, STEELS (EXCEPT CORROSION-RESISTANT STEELS), LEAD, TIN AND THEIR ALLOYS
IV COPPER, BRASS, BRONZE, (ALUMINUM BRONZE OR ALUMINUM NICKEL BRONZE), COPPER-NICKEL,
COPPER BERYLLIUM, CHROMIUM, MOLYBDENUM. NICKEL AND NICKEL BASE ALLOYS, COBALT ALLOYS,
TITANIUM AND TITANIUM ALLOYS, TUNGSTEN, CRES, CARBON, CFRP, SILVER AND GOLD

FASTENERS - FASTENER FINISH REQUIREMENTS

63-05-00
- 170 ALTEON PROPRIETARY - Copyright <d - See title page for

'.s

AlTEDN
A BOEING COMPANY

777 TRAINING MANUAL

FASTENER SELECTION (CONTINUED)
COMPATIBLE MATERIAL--FASTENERS
FASTENER
MATERIAL

STRUCTURE
MATERIAL
ALLOY STEEL, OR
ALUMINUM + STEEL

ALUMINUM +
TITANIUM

ALUMINUM

FASTENER
FINISH

ALLOY STEEL

CADMIUM OR ALUMINUM

CRES

CADMIUM

TITANIUM

ALUMINUM

OJ

ALLOY STEEL

ALUMINUM

IT]

CRES

ALUMINUM

TITANIUM

ALUMINUM

OJ
OJ

ALUMINUM

ANODIZE

ALLOY STEEL
CRES
TITANIUM

CADMIUM OR ALUMINUM
CADMIUM OR ALUMINUM
ALUMINUM
ANODIZE

OJ

MAGNESIUM

5052 ALUMINUM

ANY
EXCEPT TITANIUM

H-11 ALLOY
STEEL

NICKEL-CADMIUM (INSTALL
WITH WET PRIMER OR
SEALANT) OR ALUMINUM

TITANIUM OR
CRES

CRES
TITANIUM

COMPOS ITEI AL

TITANIUM CRES

PASSIVATE IT]
PHOSPHATE FLUORIDE
OR ALUMINUM
ALUMINUM

OJ

OJ

DO NOT USE CADMIUM PLATED FASTENERS

FASTENERS - FASTENER FINISH REQUIREMENTS

63-05-00
- 171 ALTEON PROPRIETARY - Copyright (c) - See title page for details

AlTEON
A BOEING COMPANY

777 TRAINING MANUAL
FASTENERS -- FASTENERS SECTION QUIZ
THIS PAGE INTENTIONALLY LEFT BLANK

..

>

'"
9

9

'"
'i'

'"'"

63-05-00
- 172 ALTEON PROPRIETARY - Copyright (e) - See title page for

Is

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