materiales aeronauticos
DESCRIPTION
Materiales AvionesTRANSCRIPT
MATERIALS
METALS
FASTENEPS
NONMETALS
PROTEcT ; /E TREATMEMT
OCT 9 1987 IGS C51-99-014-Q1
PR1NT DATE OCT 1988 l
ALUMINUM ALLOY APPLICATION -"707/727/737/747 AIRPLANES
General
Approximately 80 percent of the basic airframe structure is aluminum. Aluminumalloys are easily machined and fabricated compared to the steel and titanium al-loys. Aluminum alloys used for aircraft generally require corrosión protectionsystems including: (a) anodizing or chemical conversión coatings for a corro-sión resistant surface; and (b) the use of corrosión inhibiting primers andenamels.
s
The alloys of aluminum use a variety.of alloying elements and heat treatmerits toachieve an optimum combination of toughness, strength, fatigue, and corrosiónproperties for each portion of aircraft structure. The thermal and mechanicaltreatments are identified by a temper designation (TXXX) which is a suffix tothe alloy designation, e.g. 2024-T351 píate. The specific alloy systems used byBoeing are discussed below:
C51-84-532-01B 3826CSec B 4 MAR 01 1983
7075-T73 FORGINGSBODY ANO WINGS
•BULKHEAOS
• FITTINGS
VERTICAL TAIL(7075-T6)• SKINS
STRINGERS
SKIN (2024-T3)STRINGERS (7075-T6)
LOWER SKINS (2024-T3)• STRINGERS
• SPAR CHOROS(2024-T3)
HORIZONTAL TAIL• LOWER SURFACE
(7075-T6)
• UPPER SURFACE(2024-T3) (PARTIAL)
UPPER SKINS (7178/7075-T6)• STRINGERS• SPAR CHOROS
KEEL BEAM CHOROS (7075-TG & T73)
JUN 08 1987
Sec D
ALUMINUM ALLO Y/APPLICATIONS707/727/737/747 AIRPLANES
C51-84-032-01C
ALUMINUM ALLOY USAGE
1. 2024
2024 is a copper-magnesium aluminum alloy that is generally used in the naturallyaged (room temperatura aged) condition of the T3 or T4 tempers. This alloy has thebest fatigue strength and fracture toughness of the structural alloys and is conse-quently used for tensión applications such as lower wing surface and upper surfaceof the horizontal stabilizer. The body skins are also 2024 to provide máximumtoughness. Body skins are ciad to provide corrosión resistance in áreas left un-painted.
2. 7075
7075 is a copper, magnesium, zinc aluminum alloy that is often used in the -T6 orpeak aged condition for structure requiring high compression and shear strengthssuch as upper wing surface, lower surface of horizontal stabilizer, vertical stabi-lizer, and body frames and stringers. The same alloy is usud in the overaged or-T73 condition for fittings machined from forgings, píate and extrusions. The T73temper offers excellent stress corrosión and exfoliation corrosión resistance.
7178
7178peak
is a high strength copper,aged condition for
magnesium, zinc aluminum alloy that is used in theits high compressive strength. Application has been pri-
marily for upper wing surface and keel beam chord. It is no longer used for designbecause of its susceptib i 1 ity to exfoliation corrosión. Substitution of 7075-T6for 7178 requires a 15 percent increase in thickness und/or área.
356/A356/A357 Aluminum Casting
Aluminum castings are used throughout the airplane for hydraulic manifolds and con-trol linkages and are a lower cost ineans of producing complex shapes or parts.
C51-84-533-01CSec 13
9034ÍJUN 08 1987
ALUMINUM ALLOY USAGE ON BOEING AIRPLANES
ALLOYSPRODUCTFORMS
MAJORAPPLICATIONS USAGE RATIONALE
2024-T3
7178/7075-T6
2024-T3
PLATE / EXTRUSIÓN
PLATE/ EXTRUSIÓN
SHEET
7075-T6
7178/7075-T6
7075-T73
356/A356/A357
PLATE/EXTRUSIÓN
EXTRUSIÓN
FORGING/EXTRUSION
CASTING
LOWER WING SURFACEUPPER HORIZONTAL TAILSURFACE
UPPER WING SURFACELOWER HORIZONTAL TAILSURFACE
BODY
VERTICAL TAIL
KEEL BEAM CHORO
WING ANO BODYBULKHEAOS ANDFITTINGS
HYDRAULIC MANIFOLDSAND CONTROL LINKAGES
HIGH FATIGUE AND FRACTUREPROPERTIES WITH ADECÚATETENSILE STRENGTH ANDCORROSIÓN PROPERTIES
HIGH COMPRESSION YIELDWITH ADEQUATÉ FATIGUE,FRACTURE, AND CORROSIÓNPROPERTIES
HIGH FATIGUE AND FRACTUREPROPERTIES WITH ADEQUATÉSTRENGTH (TENSILE,COMPRESSION AND SHEAR) ANDCORROSIÓN PROPERTIES
HIGH STRENGTH (TENSILE,COMPRESSION, ANO SHEAR)WITH ADEQUATÉ FATIGUEFRACTURE AND CORROSIÓNPROPERTIES
HIGH COMPRESSION STRENGTHWITH ADEQUATÉ FATIGUE,CORROSIÓN AND FRACTUREPROPERTIES
EXCELLENT RESISTANCE TOSTRESS AND EXFOLIATIONCORROSIÓN AND ADEQUATÉSTRENGTH, FATIGUE ANDFRACTURE PROPERTIES
LOWER COST THAN FORGINGS,WITH ADEQUATÉ PROPERTIES
MAR 1 1983Sec B
ALUMINUM ALLOY USAGE
C51-84-033-01A
ALUMINUM ALLOY APPLICATIONS - 737-300/757/767 AIRPLANES
General
The 757/767 and the new 737-300 airplanes use improved alurainura alloys for wingstructure and forged fittings. These alloys are based upon earlier alurainura alloysand use similar but refined chemistries in addition to special processing controls(such as therraomechanical treatraents, etc.) to improve properties. The alloys usedon the 707/727/737/747 are still used in the body and other áreas as described inthe earlier section. The five new improved alloys are as illustrated.
These improved alloys often will not be available for use in repair applications.The 2024T3/T4 and 7075-T6 alloys may be used as substitutos by increasing the áreasand/or thickness by 15 percent./
C51-84-534-01CSec B
9034ÍJUN 08 1987
7075-T73, 7050-T7367175-T736 FORGINGS
BODY ANO WINGS• BULKHEADS• FITTINGS
LOWER SKINS (2324-T39 PL)• STRINGERS• SPAR CHOROS
(2224-T3511 EXTR.
VERTICAL TAIL7075-T6• SKINS• STRINGERS
HORIZONTAL TAIL7075-T6• SKINS (LOWER)• STRINGERS
2024-T3 (PARTIALUPPER SKINS)
tIPPER SKINS (7150-T651 PL.)STRINGERS(7150-T65I1 EXTR)
KEEL BEAM CHOROS (7150-T6)
JUN 8 1987Sec B
ALUMINUM ALLOY APPLICATIONS737-300/757/767 AIRPLANES
C51-84-034-01C
A I . U M I N U M A L L O Y USAGli 757 /767
1. 2224 1-xtrusion
This alloy has higher tensile strength, fatigue and fracture properties than thebaseline 2024 extrusions with equivalent corrosión resistance. The materialstrength and toughness is achieved by tighter control of chemical compositionand application of special process controls during fubrication.
2. 2324 Píate
This alloy has higher tensile strength and fatigue properties than the baseline2024 alloy with equivalent fracture and corrosión resistance. The materialstrength is achieved by thermomechanical processing, i.e., cold work and pre-cipitation hardening.
3. 7150 Píate and Extrusión
This alloy has higher compressive strength than baseline 7075 alloy with equiva-lent or better fracture properties and corrosión resistance. The materialstrength is achieved by tighter control of chemical composition and applicationof special process controls during fabrication.
-1. 7050 Forging
This alloy is used primarily for thick section forgings greater than 3.0 incheswhere additional strength may be utilized. The alloy has equivalent fatigue andfracture properties to the baseline 7075-T73 when used as 7050-T736.
5. 7175 Forging
This alloy is used primarily for forgings less than 3.0 inches where additionalstrength may be utilized. The alloy has equivalent fatigue and fracture proper-ties to baseline 707S-T73 when used as 7175-T736.
C51-84-535-01Ü 3474CSec b 10 MAR 01 1983
ALLOYSPRODUCTFORMS
MAJORAPPLICATIONS USAGE RATIONALE
2324-T392224-T351
7150-TG
2024-T3
7D75-T6
7075-T6
7150-T6
7075-T73,
7050/7175-T736
3G5/A356/A357
PLATEEXTRUSIÓN
PLATE/EXTRUSIÓN
SHEET -
PLATE/EXTRUSIÓN
PLATE/EXTRUSIÓN
EXTRUSIÓN
FORGING
FORGING
CASTING
LOWER WING SURFACE
UPPER WING SURFACE(
BQDY
HORIZONTAL TAIL
VERTICAL TAIL
KEEL OEAM CHORO
WING AND BQDYFITTINGS
WING ANÜ BODYBULKHEADS ANO FITTINGS
HYDRAULIC MANIFOLD ANDCONTROL LINKAGE
HIGHER TENSILE STRENGTHTHAN 2024-T3 WITH ADEQUATEFRACTURE, FATIGUE ANOCORROSIÓN PROPERTIESHIGHER STRENGTH THAN 7178/7075-T6 WITH AOEQUATE FATIGUE,FRACTURE AND CORROSIÓNPROPERTIES
NO CHANCE - SAME RATIONALEAS FOR QTHER AIRPLANES
HIGH STHENGTH WITH ADEOUATEFATIGUE, FRACTURE, ANOCORROSIÓN PROPERTIES(SIMILAR TO OTHEHAIRPLANESÍ
NO CHANCE - SAME RATIONALEAS FOR QTHER AIRPLANES
HIGHER COMPRESSION STRENGTHTHAN 717B/7075-T6, WtTHAOEOUATE FATIGUE ANOCORROSIÓN PROPERTIES
NO CHANCE - SAME RATIONALEAS FOR OTHER AIRPLANES
HIGHER STRENGTH THAN 7075-WITH EQUIVALENT FATIGUE ANDFRACTURE PROPERTIES
NO CHANCE - SAME RATIONALEAS FOR OTHER AIRPLANES
MAR 1 1983
Si-c: D
ALUMINUM ALLQY USAGE 757/767C51-84-035-01A
11
ALUMINUM ALLOY IIEAT TREATMENT
The primary operations or processes in the heat treatment of an aluminum alloyare solution heat treatment and age hardening. ,
Solution treatment consists of heating the aluminum part to 800 to 900 degreesF. (depending on the alloy) and quenching the part in cold water. Occasionallyparts are quenched in hot water to reduce the resultant part distortion orwarp. Hot water quenching should not be allowed with 2024 alloys since the re-duced cooling rate lowers the resistance of 2024 material to exfoliation corro-sión.
The part is then aged to increase its str.ength. Sotne alloys will naturally ageat room tempera ture. Other alloys and tempers mus't be artificially aged in anoven. The artificial aging tempera tures vary from 250 to 350 degrees F. depend-ing on the alloy and temper condition desired.
An abbreviated chart of the aluminum temper designation system is shown.
The only heat treat designations that Boeing or the airlines can accomplish arethe -T42, -T62 or the -T73 conditions.
C51-84-543-01 9034ÍSec B 12 MAY 02 1984
-T6
STANDARD HEAT TREATEDDESIGNATION.
TEMPER DESIGNATION
-T3: SOLUTION HEAT TREATED. COLÓ WORKED ANDNATURALLY AGED.
-T4: SOLUTION HEAT TREATED AND NATURALLY AGED.
-T42: SOLUTION HEAT TREATED AND NATURALLY AGEDBY THE USER. APPLIES TO 2024-0 AND 6061-0.
-T6: SOLUTION HEAT TREATED AND THEN ARTIFICIALLYAGED. NOT APPRECIABLY AFFECTED BY COLÓ WORK:FOR MOST MATERIALS THE -W AND -T4 TEMPERSARTIFICIALLY AGE TO -T6.
-T62: SOLUTION HEAT TREATED AND THEN ARTIFICIALLYAGED BY USER. APPLIES TO A NUMBER OF ALLOYS (E.G.2024. 6061. 7075), WHICH HAVE BEEN HEAT TREATEO ANDAGED BY USER.
INDICATES MINOR STRAIGHTENINGUSE TO MEET STRAIGHTNESS ANDFLATNESS TOLERANCES. THIS DIGITIS OIF NO STRAIGHTENING ISALLOWED.
MATERIAL WAS STRETCHED TOACCOMPLISH STRESS RELIEF. THEOIGIT 2 WOULD BE USED HEREWHEN COMPRESSIVE METHODS AREUSED.
INDICATES MATERIAL HAS BEENSTRESS RELIEVED.
-T73: SOLUTION HEAT TREATED AND OVERAGED.THIS TEMPER APPLIES TO SEVERAL 7000 SERIES ALLOYSAND INDICATES A GREATER DEGREE OF OVERAGING RE-QUIRED FOR HIGHER STRESS CORROSIÓN RESISTANCE.MATERIAL IN THIS TEMPER IS ALSO IMMUNE TO EXFOLI-ATION CORROSIÓN. AS APPLIED TO 7075 OR 7175. THE-T73 TEMPER IS VIRTUALLY IMMUNE TO STRESS-CORROSION.
SEP 29 1987Seo B
ALUMINUM ALLOY HEAT TREATMENT
C51-84-061-01A
13
ALUMINUM WELDING
Welding
Welding of 2000 and 7000 series aluminum alloys is not permicted. The weldingprocess changes the structure of the metal and produces a permanent loss-of properties for these alloys. Other alloys such as 6061 are weldable and may be weldedper the Repair Manual. See the appropriate Boeing documents for specific restric-tions and áreas approved for welding.
C51-84-536-01E 9034ÍSec B 20 JUN 08 1987
WELDING
fulIon -
Utld rtpilrltif o' Ptrtt ind
I) UK 11 H.i) Renoit d(((Ct b/ qrmdl
irod i f I f d.]J Wtld recilr «hen u H
Conildcr huí un
WU01IJGc-í nttill ptr BU
ordfr o' prt'trenct:
r i l lng» drlllliq. tic,. *nd trien uir it
{ondidon oí Piri.«nd multint propfrftt l m trie r . j í i f í c t t r : roñe.
lptctlon M rcnulrttl J Í . ÍT- i^, T- . - -:: U«ri> «ccampl i ir>ed.
-f - A -* U rvp4lr M fltcriljry, .-j- ' . . ' ¡ . . ..'..-! 11 (he • -— . - r lniInj<Honu
U Prcclfinin^ prccen.? ) T I O L . - I S ] prflf tu ,1' Fll l tr «cltl (üfld rod :.',:;4) D«1niptct1oi ftquirrMentt.5) A ilflt«B«nt iptci'ring timt^ t rt-*en
1113 tic rvtglUnl rvduc e4 -v. ' c - • i . irocijont -••.-'- rué pirt li.jn * h«t trri^td
, procedurtí mil t4
in ' . • = tett ji.jn orlar la
CAUIION: Pri '%1'. tlruClurtl pin« -.-.IU . nol M -flJDotlfig J^prnvjl.
TI - tA l -4* . «rauin'i]tfld C4K Pírll 'ii-;ov-íí«-i>i _ :_Camrcul \i purtIIURHa,• . - JA ' -: ;: lubm
rfgurM -ItlKlul
L¿_J Furn.ct itnn nli*r rciuiríd lor clllt '»• -*ldi. HMKIIinti (orclin 'B' -fluí.
NO!E: Ir» -tliWnt ifull t» p)ittd in ih« ilnii nlltf (urnict mcfl ihitIhe Htld riott no< coa I bílan t'1* ^>ninj» prvhcit tarveriturt un I i I
í ) > Í5ÍI-IÍ 11 luDJicl U c r j ; i i n ) »ntn .tldti. Uit .fl or -14 Icrotrl.S o i t L l o n nui ind iqe :o -Ti candillaii ir'ítr Hcldlng ur ilnplí <gt tathe -T6 ifttr wrltflng if luiinB joinl itrtngth ll ~'0i requinte.
I ti sni i j .-oí M »t*t itf í iba» Ui» 160 - ZOO «i Irtij*.
JUN 08 1987Scc B
ALUMINUM WELDING
CS1-B4-036-01C
21
TITANIMUM ALLOY APPLICATIONS
Titanium (Ti) alloys are used in a variety of structural and non-structuralapplications in Boeing airplanes. Titanium alloys are used generally for one ormore o£ the following reasons:
excellent corrosión resistanceweight-savingselevated temperature stabilityto alleviate volume constraint problemscompatibi1 ity with other materials
Titanium alloys are ver y corrosión resistant and do not p i t from cor'rosionprocesses. Titanium alloys are approximately 40% less dense than steel so thatweight savings are often realized by using titanium alloys ruthe,r than steels.They are used in place of aluminum alloys when:
(1) elevated temperature stability is required;(2) an aluminum alloy component would be too largo to intégrate into the
overall structure and a titanium alloy component would fit; and/or,(3J aluminum alloy is not desired to be in direct contact with another
material for galvanic corrosión reasons.
C51-84-537-01A 3489CSec B 22 MAR 01 1983
APU FIREWALL
MAIN LANDING GEAR BEAMSAND ASSOCIATED STRUCTURE
WINDOW SILLAND POSTS
OUTBOARD FLAPSUPPORT LINK
INBOARD FLAPSUPPORTLINK
ELEVATORACTUATORFITTINGS
INBOARD AUXILARYSLAT TRACKS
- MLG ACTUATOR SUPPORT FITTINGS- FORWARD LANDING GEAR TRUNNION
BEARING HOUSING '
MAY 19 1983Sec B
THRUST REVERSER FITTINGS
HYDRAULIC LINESSPRINGSFITTINGS (STRUCTURAL ANO NON-STRUCTURAL)PNEUMATIC DUCTSFASTENERS
fTITANIUM ALLOY APPLICATIONS!
C51-84-037-01B
23
TITANIUM ALLOY USAGU
There are a variety of titanium alloys chosen for specific applications basedupon needed material properties and a balance between «atería!/fabricación costsand component weight. The follouing are the primary alloys used by Boeing, thetypes of applications, and the reasons for selection.
Commercially Puré (CP) Ti - is the lowest strength titanium grade used byBoeing. CP Ti is used for applications such as scuff plates and pneumaticducts. CP Ti is also employed for many fittings and clips in áreas of highercorrosión potential such as near galleys and lavatories.
TÍ-3A1-2.5V - is used on the 757/767 for high pressure hydraulic tubing toreduce weight oyer tlie previously used stainless steel tubing.
TÍ-6A1-4V - is the most cxtensively used alloy. There are three heat treat-ments used depending upon tlie specific requi rement for component. Applica-tions for this alloy include:
(1) Windshield'frame for 757/767; 767 floor support structure;(2) landing gear beam for the 747 $ 757; and(3) 767 APU firewell; a variety of structural fittings, fasteners and
hydraulic fittings.
Ti-6A1-6V-2Sn - is higher strength than TÍ-6A1-4V which allous more weightsavings. Ti-6A1-6V-2Sn is used primarily on fittings on the 747 landing gearand wing área as well as extensive use in the flap support structure on the747SP.
C51-84-538-01A Sht 1 3492CSec B 25 MAR 01 1983
TITANIUM ALLOY USAGE
Ti-10V-2Fe-3Al - is a newer titanium alloy with higher strength than eitherTi-6Al-6V-2Sn or TÍ-6A1-4V. This newer alloy is used in forgings in the 757Trunnion Dearing Housing, Auxiliary Slat Tracks, and Door Hinges and will beused in the 737-300 in the Overwing Nacelle Fitting. Ti-10V-2Fe-3Al, because ofits higher strength, offers more weight savings. Because Ti-10V-2Fe-3Alexhibits improved low temperature forging characteristics over TÍ-6A1-4V it isan attractive material for near nct shape precisión forgings.
Ti-13V-1lCr-3Al is used in the 747, 757, and 767 airplane in spring applica-tions. This alloy is used as a spring material because its low modulus o£elasticity and reduced density allows up to 70*. weight savings over steel.
C51-84-538-01B Sht 2 3500CSec B 26 MAR 01 1983
TITANIUM ALLOYS USEO ON BOEING AIRPLANES
ALLOY
COMMERCIALLYPURÉ TI
TI 3AL-2.5V
TI-6AL-4V
TI-6AL-6V-2SN
TI-10V-2FE-3AL
TI - I3V-1 ICR-3AL
HEAT TREATCONOITION
ANNEALEO
COLD-WORKEO ANOSTRESS RELIEVED.ANNEALEO
ANNEALEOBETA ANNEALEOSOLUTIONTREATEOAND AGEO
SOLUTIONTREATED ANDAGED
SOLUTIONTREATEO ANDAGED
SOLUTIONTREATED ANDAGED
STRENGTHRANGE. KSI
50-80
100-125
120 160
150 170
180
200-230
• FORMS
SHEET. STRIPPLATE
TUBING
SHEET, PLATE.FORGINGS, EXTRU-SIONS, CASTIÍIGS
PLATE ANDFORGINGS
FORGINGS
SPRINGS
APPLICATIONS
SCUFF.PLATES. DOORTHRESHOLOS. PNEUMATIC OUCTS.FIREWALLS. MISC. NON STRUC-TURAL FITTINGS.
HIGH PRESSURE HYORAULICTUBING ON 757. 767
LANOING GEAR ÁREA.FIREWALLS. NO. i WINOSHIELDFRAMES ON 757 AND 767. FLAPFITTINGS. 767 FLOOH SUPPORTSTHUCTURE. MISC. STRUCTURALFITTINGS. HYORAULIC FITTINGS,FASTENERS
USED PRIMARILY ON747. FITTINGS INLANOING GEAR ANOWING ÁREA. USEOEXTENSIVELY ON FLAPSUPPORT STHUCTUREOF 747 SP
757 TRUNNION BEARING HOUSINGAUXILIARY SLAT TRACKS DOORHINGE MECHANISM737-300 OVERWING NACELLEFITTING
747. 757. 767 SPRINGS INLANOING GEAR ANO DOOR ÁREAS
USAGE RATIONALE
BETTEH STRENGTH TO WEIGHTRATIO THAN STAINLESS; EXCELLENT CORROSIÓN RESISTANCE;FORMABLE
WEIGHT SAVINGOVER STEEL
WEIGHT SAVING OVERSTEEL: VOLUME CONSTRAINTSOF Al.
HIGHER STRENGTH THANTI 6AL-4V THEREFORE GREATERWEIGHT SAVING
WEIGHT SAVING
WEIGHT SAVINGOVER STEEL
^MY 19 1983Sec D
TITANIUM ALLOY USAGEC5184038-01B
27
UNIQUE IIANDLING CIIARACTL-RI STICS OF TITANIUM ALLOYS
1 . Genera 1
2. Stress Relieve after Cold-forming or Straightening
Straining of titanium alloys can cause a signifigant drop in the yield strengthdue to a me tal lurgical phenomenon and introduces high residual stresses. Stressrelieving removes these effects and restores the original properties. Stressrelief is not required for the CP alloys.
3. Weld in Protective Atmosphere or with Shielding Gases
Without inert gas p r o t e c t i v c shielding during wulding, t i tan ium alloys can pick-up oxygen or hydrogen. Meat-treated alloys must be reheat created after weld-ing. See SIIM for requi remen ts .
4. Assure Protective Coating Integrity on Potential Skydrol Exposure Áreas
In áreas where skyclrol exposure at eleva ted te m p e r atures can, occur, a protectivecoating is used to prevent the skydrol from contacting the titanium alloy. Theprotective coatings must be continuous to be effective.
5. Use Caution Wlien G r i n d i n g Titanium Materials
Grinding as a final f i n i s h operación must be done with care. The grindingoperation can produce both: (a) high tensile stresses at the surface whichaids early crack i n i t i a t i o n , and (b) surface damage in the form of small tearsunless adequate precautions are taken. Overhaul Manual Section 20 describes theacceptable methods to be used for metal removal.
CS1-84-539-01B 9034?Sec U 28 JUN : 1987
WELDING - NO
GRINDING - WITH CARE
REQUIRES INERT GAS PROTECTIVE SHIELDING
JUN 08 1987Sec B
UNIÜUE IIAIMDLING CHARACTERISTICS OF TITANIUM ALLOYSC51-84-039-01D
29
STEEL APPLICATIONS
Approximately 12-16 percent of the basic airplane structure is alloy steel andstainless steel. The high strength and high modulus of elasticity are theprimary advantages of the high strength steels. The high strength and modulusare useful for designs with space limitations such as with some landing gearcomponents.
Alloy selection considera tions include service temperature, strength, stiffnessfatigue properties and fabricabi1 ity.
C51-B4-540-01A 3518CSec B 30 MAR 01 1983
INBOAHD FLAP TRACKS.4340M
FLAP LINKAGE.15-5PH ANO4330M
REAR ENGINE MOUNT,9 NI-4CO-.30C
HYDRAULIC LINES
LANDING GEAR4340M
FRONT ENGINE MOUNT, STRUT LOWERSPARS. WEB, AND CHOROS,15-5PH
ENGINE MIDSPARATTACH FITTINGS,4330M
•SLAT TRACKS.4340M
OCT 24 1983Soc D
STEEL APPLICATIONS
C51-84-040-01A
31
STEEL ALLOYS AND TEMPERS
Material Designations
given to most low alloy steels are based upon an AISI (AmericanInstituto) system that refers to the chemical composition of the
alloy. The first two digits refer to the specific primary alloying elements,the last two (and the last three digits in a five digit number)percentage of carbón contained in the alloy.
DesignationsIron 5 Steel
refer to the
10XX -41XX -43XX -52100 -93XX -
r examp]
refers to plrefers to chrefers to nirefers to arefers to af eren t ra t i oloys) .
Le; 4340 refersperccnt carbón.
plain carbón steels (contain only carbón and manganese)chromium and molybdenum alloy steels
;1, chromium and molybdenum alloy steelschromium alloy with 1.00 percent carbónnickel, chromium nnd molybdenum alloy steel (with a d i fbetween these ulcmcnts than contained in the 43XX al-
to a nickel, chromiuin, molybdenum allpy containing .40
9Ni-4Co.30C.30 percentcobalt in the
is a specific trade ñame assigned to a nickel - cobalt alloy withcarbón. The 9 and 4 reí?cr to the nominal percentajes of nickel and
alloy.
The normally used low alloyshown. Use of these alloys
steels andis limited
tlieir applicable strength ranges areto the strength ranges shown.
C51-84-546-01Sec B 32
9034ÍMAY 02 1984
LOW ALLOY STEELS AND THEIRAPPLICABLE STRENGTH RANGES
ALLOY
4340
4330M
9Ni-4Co-.30C
4340M
STRENGTH RANGE (KSI)
125-145
X
150-170
X
X
160-180
X
180-200
X
X
220 MIN
X
X
275-300
X
JUN 08 1987Seo D
STEEL ALLOYS ANO TEMPERS
C51-84-046-01A
33
HEAT TREATING STEEL
When steel is heat treated its crystalline structure undergoes various phasechanges. This chart shows the various phases for different carbón content tempera-ture combinations. When steel is heated it will pass through these phases. Ifcooled at a slow rate it will go through the same phase changes in the reverse di-rection. However, if a part is quenched in cold water or oil the material cannotdo a complete phase reversal. It will remain as austenite until tempera tures of600°F or below are reached. Mere the austenite begins to transforin into a consti-tuent called martensite which is responsable for the hardness of quenched steels.
Tempering of this steel is necessary to relieve the resulting 'residual stressescaused by the quenching and to impart toughness to the steel in contrast to thebrittleness of martensite. The structure produced by tempering a quenched steel iscalled tempered martensite.
C51-84-571-01 34 9034ÍSec B JUN 08 1987
LIOUIO AND FEHRITE
FERHITE
FERRITE ANDAUSTEHITE
AUSTENITE
AUSTENITE ANDFERRITE
FERHITE
JUN 08 !!18/Siv II
3.0 3.5 1-0 1.5 5.0
WCIGI IT l 'LRCLNT CARHON
LLinuiD
1 I J LCCMENTITE
LIQUID
L.IQUID ANDAUSTENITE
LIDUin ANDCEMENTITE
AUSTENITE ANDCEMENTITE
FEHRITE ANDCEMENTINE
HEAT TREATING STEEL
CSI-8-1-0/1-U1
l'RIMARY STEELS USLD 1N BOEING A1RPLANES
The most w i d e l y used high strength steels are 4330M heat t r e a t e d to 220-240 ksiand 434QM lieat treated to 275-300 ksi. For elevated -tempera ture applications upto 900F, such as aft.engine mpjjnts, 9Ni - 4Co-0. 30C steel h e a t treated to 220-240ksi is used. The 5ucc«atKÍ*euSe of high strength steel is attributed to carefuldesign and stringent m a t e r i a l and process controls.
\'' (, r. ->??*
For bar and forging applications at strength level of 200 ksi or lower, 15-5PHprecipi ta t ion hartlening stainless steel is currently being used in place ofa 11 oy s t e e l , M anufacturing costs are reduced by using 15-5PII and improvedcorrosión resistance is obtained.
For a p p l i c a t i o n s r e q u i r i n g sheet, 15 - 5PH is used for thicknesses of 0.063 indiand ovcr. H o l l i n a of 15-51'H lo t li i cknessc s undur 0.063 inch is not p r a c t i c a ! ,lio til 1 7 -<1 1>̂ | and 17-7 P̂ ( a 1 ) oy:> con Ui l n ilt; 1 t;i f c r r i ti: i nc I us i ons wh i cli causeuns tabl e transverso mechan i c a 1 propc r t i es . SÍ nce Lli i s i s a mi ñor prob 1 c.w i n Lhot li i n n¡¡ uyi;i) I 7 - 7 I'II l S iisml i n LltJCKllCSStiS luí 1 o u O . OÍJ 3 i ncli ¡uní i s of IUIL a I 1 out,'tlas a s u b s t i t u t e for 15-51*11 in gauges up to 0.10 inch.
300 se r i (>s JI..H.S tt;n i t i c s t a i n l e s s steel sheet .,.„ t, .,„„,, ... ~ ,._,„„ ,. ~. ,„„j th appl i ca t i ons w lie re cor ros í on or hyg i ene c once rus díctate m a t e r i a l
needs, 4 1 3 0 a n i l ' 1 3 4 0 a l l o y s i e o l s h c e tcons t rúe t i on.
ni a t e r í a i s are used for lowerconce rus
m a t e r i a l is ra reí y used in a i r c r a f t
Tb e 727, 737 and 747 use 21-6-9 ¡insten i t i c stainless steel for liydraulic tubingappli catiónS, 17 - 4 IMI preci pi ta t ion hardening stainless stee) i nves tmen t cast-ings h e a t t r e a t e d to 150 ksi or 180 ksi m i n i m u m are also used where a p p l i c a b l e .
C51-84-541-01CSec B 36
9034ÍMAR 03 1986
C
STEEL USAGE ON BOEING AIRPLANES
ALLOYS
4340M
4330M
9NI-4CO-0.30C
15-5PH
2 I - G - 9304/321/347
15-5PH
17-7PH
304/321/347
17-4PH
(KSI)STRENGTH
275-300
220-240
220-240
180-200150-170
I42 -1G275 MIN.
180-200150-170
180-200150J70
75 MIN.
180-200150-170
FORMS
BAR AND FURGING
BAR AND FORGING
BAR ANO FORGING
STAINLESS S T E E LBAR AND F O R G I N G S
TUBING
SHEET
SHEET
SHEET
CASTINGS
APPLICATIONS
LANDING GEAR COMPONENTSFLAP TRACKS. FLAPCARRIAGES, FITTINGS
AFT ENGINE MOUNTS
ACTÜATORS, ROD ENDS,FITTINGS, MECHANISMS
IIYDRAULIC SYSTEMS,INSTRUMENT LINES
LAVATORIES AND GALLEYS,DOOR THRESHOLDS, STRAPS
LAVATORIES AND GALLEYS,DOOR THRESHOLDS, STRAPS
LAVATORIES AND GALLEYS,DOOR THRESHOLDS, STRAPS
CONTROL LEVERS,FITTINGS, HOUSINGS
'V
USAGE RATIONALE
HIGH STRENGTH TO WEIGHTRATIO AND HIGH MODULUS OFELASTICITY
ELEVATED TEMPERATURESTABILITY AND HIGH STRENGTH
CORROSIÓN RESÍSTANLEAND HIGH MODULUS
CORROSIÓN RESISTANCE.FABRICABILITY. ANDHIGH STRENGTH
CORROSIÓN RESISTANCE,HIGH STRENGTH,AND FABRICABILITY
UTILIZED WHEN THICKNESSISLESSTHAN 0.063
FABRICABILITY, HYGIEÑIC NEEDS
CORROSIÓN RESISTANCE,AND FABRICABILITY
MR 1 1983>ec D
PRIMARY STEELS USED IN BOEING AIRPLANES
C51-84-041-01A
37
STEEL ALLOY REWORK PRECAUTIONS
The following precautions must be observad when doing rework operations on steelparts.
\Stress Concentrations
Since most steel parts are highly stressed localized stress concentrations areundesirable and should always be removed.
Hydrogen Embrittlement
Do not introduce hydrogen into the part. If any question exists as to its in-troduction the part must be baked at 375°F for at least 3 hours. This tempera-ture, incidentally, will not harm either paint, or shot peening.
Untempered Martensite
Caution must be exercised whilst reworking the low alloy carbón steels so as toprevent the formation o*f untempered martensite or the generation of undesirableresidual tensile stresses. Any metal removal should be done by hand or withslow speed handheld power tools.
The processing of steel parts is very critical and must be done in the propersequence. The engineer must spell out exactly what work is to be done includitemperature and time limits.
C51-84-551-01 46 9034ÍSec B MAY 02 1984
• STRESS CONCENTRATIQNS
• HYDROGEN EMBRITTLEMENT
• UNTEMPERED MARTENSITE
• STRICT PROCESS CGNTROLS
MAY 02 1984
Süc B
47
STEEL ALLOY REWORK PflECAUTIONS
C51-84-05101
FASTENERS
55
FASTENERS
Fasteners are classified in two basic types; removable and permanent.
Removable fasteners consist of bolts or screws installed with núes or nut plates.Such fasteners inay be removed and reinstalled.
Permanent fasteners consist of hex-drive bolts (Hi-Loks), Lockbolts and Rivets.This type of fastener must have one element of the system destroyed in order toremove it, therefore it is not reusáble.
Removable Fasteners:
Within the removable fastener category are fatigue rated,rated bolts.
tensión rated. and shear
Fatigue rated bolts have 12 point protruding heads with long threads. They areavailable in strength ranges of 160 to 220 KSI tensile strength. Materials arealloy steel, GRES (A286, Inconel 718), 6AL4V titanium or H-ll steel.
Shear and tensile rated bolts may have hex, 12 point or countersunk heads with longthreads for the tensile and short threads for the shear rated. Materials optionsare the same as for the fatigue rated bolts. All Boeing standard bolts have rolledthreads.
Fasteners that are fully threaded, regardless of head style, are usually consideredscrews. Screws are available with hex heads, pan (round) head, flush heads orsocket heads. Recesses are Phillips, Mi-Torque or hex (Alien). Materials arealloy steel, GRES, titanium or aluminum. Strength levéis to 160 KSI tensile and 95KSI shear are available.
Note that screws are not used for structural load transfer.
C51-84-501-01DSec B
56 9033ÍJUN 08 1987
COUNTER SUNKHEAO BOLT
SHORT THREADS
\
LONG THREAD (TENSIÓN)SHGRT THREAD (SHEAR)
SHQRT THREADS
— 1
12 PT MEAD BOIT - LONG THREAD (TENSIÓN)SHORT THREAD (SHEAR)
LONG THftEADS
pp
HEX HEAD BOLTS - LONG THREAD (TENSIÓN)SHGRT THHEAD (SHEAH)
12 POINT HEAD FATIQUE-TENSION BOLT
ALL "BAC" BOLTS ARE PunCHASEOWITH ROLLEO THREADS.
JUN 08Sí:c B
57
FASTENERS
C51-84-001-01C
IIARD FASTENER ALLOYS
The hard fastener alloys together witli the applicable shear and tensilestrengths are summarized for convenience.
CS1-84-552-01 9034ÍSec B 58 MAY 02 1984
ALLOYS'
STEEL
8740/4340
H 11
CRES
A286
PH 13-fl MO
INCONEL 718
TITANIUM
'6AL4V
. MÍNIMUM RATEO STRENGTH - KSI
SHEAR
95
125
95/110
125
102/125
95
TENSIÓN
160
220
160/200
220
180/220
160
MAR 03 1U8G
Stv H
59
HARO FASTENER A L L O Y S
C51 84 052 O ÍA
NUTS/NUT PLATES
Nuts are generally classed as tensión or shear. Tensión nuts are available instrengths 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 matingbolt or screw. Nut plates are used in "cióse outs" or other places with limitedor no access. They are attached with rivets. Nutplates are predominately inshear applications and are predominately of 125 KSI strength with a limited num-ber rated at 160 KSI.
CS1-84-S02-01A 3457CSec B 60 MAR 01 1983
TENSIÓN NUT SHEAH NUT
NUTS
NUTPLATES
OCT 24 1383
Set: B
NUTS/NUTPLATES
C5I-84-002-OIA
61
PERMANENT FASTENERS
Hi-Loks, called hex-drive bolts by Boeing, are installed with collars having afrangible hex that "shears off" at a predetermined torque valué. The collar has nomeans of removal other than destruction. One advantage is that no torque wrenchesare required for installation. Self-locking nuts can be, and sometimes are, usedin place of collars. Materials f.or the pins are titanium, alloy steel, GRES, andaluminum. Collars for Hi-Loks are of aluminum, 300 series GRES and A286 GRES.
Lockbolts are optional to shear Hi-Loks. The lockbolt is inherently fluid tight,including fuel. The tensión lockbolt uses an aluminum collar and is lighter thanthe tensión Hi-Lok, which uses a GRES collar. Lockbolts are available in titanium,alloy steel and A-286 GRES. Pulí type lockbolts require more clearance for instal-lation tooling than Hi-Loks.
C51-8-1-503-01B c^ 9033ÍSec B JUN 08 1987
LOCK80LTS HI-LOKS
TENSIÓN - PROTRUDING MEAD
TENSIÓN- FLUSH HEAO
fflTENS1QN-PROTRUDING MEAD
h-TENSIÓN - FLUSH MEAD
SHEAR - PROTRUQING MEAD SHEAR - PROTRUD1NG MEAD
Ili 1SHEAR - REOUCED FLUSH HEAO SHEAR - REDUCCD FLUSH HEAD
JUN 08 1987
Soc B63
PERMANENTFASTENEflS
C51-840G301B
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industrialf asten-írsConstrocfipn
The ilhtstraiion below, depicts lypical and common aircraft ( AN and ÑAS ) typeand their ideniilying niarkings.
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materials innovation
Hex Bott Identification Cuide
Hardware Menú | Products and Services DirectoryBump Thread Metric Machine ScrewPatentad prevailmg lock thread Enhanced S reusable locking action Rnd everythmg vou need to know about Screw Machine Produc
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Note: Some bolts share identical head Identification and have significanliy differem strengths.
IdentificationGrade Mark
^S1 s X. JV >^^
fT»r ii 1k ¿
^^.̂X
í??^,<^I jv^>7^'• u.!> i!v,,x
Specifícation
S.\EJ429•!c 5
ASTM A44Q
SAE J429Grade 5.!
SAh J42*íGrade 5.2
ASI'Vl A325-(.'. \
ASTM A325Type 2
Description
Bolts, Screws,Studs
fSems
Bolts,Screws,
Studs
High StrengthStructural Bolts
Higli StrengthStructural Bolts
Material
Médium CarbónSteel
Low or MédiumCarbón Steel
Low Carbón
Médium Carbón
Low Carbón
ProofLoad
S5 C74. •' '
-
85.000
.
S5.000
VieldStrengthMin (psi)
92,000thru 8 1 ,000
92,000
92,000thru 81,000
92,000
-- TensStren;Min (|
'
1 20,0
.