Determination of Monitoring Parameters for Fatigue Behavior of Steel-Concrete Composite Bridge Girders with Welded Full Depth Transverse Sti ﬀ eners

: In this study, parameters that should be monitored during the service life of a bridge and the relationship between the parameters and damage are investigated in order to predict the fatigue damages in steel-concrete composite bridge girders with welded full depth transverse sti ﬀ eners. In this context, static and fatigue tests are carried out on steel-concrete composite beam specimens with welded full depth transverse sti ﬀ eners. Load-deﬂection behavior of specimens is determined by these monotonic tests. In the fatigue tests, the specimens are subjected to cyclic loading with various stress ranges, and stress range - number of cycles (S-N) data is obtained. Fatigue crack and fatigue fracture are observed in the ﬁrst two specimens with the highest stress range applied. As expected, the fatigue crack occurred at the point where the sti ﬀ ener is welded to the bottom ﬂange. During the tests, dynamic deﬂection and strain measurements are performed at the critical points throughout the cyclic loading. The parameters which are more critical in terms of fatigue behavior and should be monitored are determined by examining the relationship between the obtained data from these measurements and fatigue damage. Discussions and evaluations are made on the level of safety presented in the relevant code by the comparison of the obtained results from fatigue tests with the code and the important studies in the literature. Finally, the specimens without fatigue fracture were tested under monotonic loading to determine the residual strength. Accordingly, the change in the load-deﬂection behavior after cyclic loading is demonstrated.


Introduction
Fatigue of metallic materials is an essential factor that affects the service life of many engineering structures. The first systematic studies on fatigue are made by August Wöhler in the 1850s and 1860s. Wöhler found the concept of stress range-number of cycles diagram (S-N) and showed that the fatigue behavior depends on the stress range rather than the highest stress [1]. In the 20th century, the fatigue mechanism of metallic materials began to be examined with the advances in the microscopic examination. The formation of a fatigue mechanism has been observed in materials exposed to cyclic loads. In this mechanism, initially, micro-cracks are formed which cannot be seen macroscopically. These cracks grow and cause the collapse of the element over time [2].
Welded steel bridges, which are highly prone to fatigue, have been built frequently since the 1950s [3]. In the 1960s, the first fatigue cracks began to be seen on the beams with stiffened flanges. In the 1970s and 1980s, fatigue cracks are frequently encountered on the other welded connections.
Five tests (one monotonic and four cyclic) are performed within this context. Initially, the load-deflection behavior of the specimens is determined by the monotonic test. Then, the fatigue behavior of the specimens is examined by subjecting the specimens to the cyclic loads at various stress ranges. The fatigue fracture occurred in two specimens with the highest stress range applied. In the cyclic loading tests, deflections and strains at the critical points of the specimens are measured during whole loading. The type of the structural health monitoring technique that should be used and the type of the data that should be monitored with these systems are determined by examining the relationship between the data obtained from these measurements and fatigue behavior. The results obtained from fatigue tests are compared with AASHTO LRFD [8], and general discussions are made about the level of structural safety presented in the code. In addition, after cyclic loading, the specimens without fatigue fractures are examined under monotonic loading to determine the change in the residual performance. The presented work is a part of a PhD. Thesis of Istanbul University [59].

Material Properties
In this section, properties of the concrete, steel and rebar materials used in this study are presented. Five standard cylinder concrete samples (150 × 300 mm) are tested 28 days after casting to achieve the compressive strength of concrete in the scope of material tests considering the recommendations presented in TS EN 12390-3 [60]. Six coupon samples are taken from the web and flange of the steel sections, and tensile tests are performed on these samples according to the rules given in TS EN ISO 6892-1 [61]. Five rebar tensile tests are performed to obtain the material properties of rebar used in the specimens based on the rules presented in TS EN ISO 6892-1 [61]. The average values of the obtained properties for concrete, steel section and rebar materials are summarized in Table 1. The standard deviation of the concrete strength and modulus of elasticity of concrete are 2.56 and 440 MPa, respectively.

Specimen Design
The scale of the produced specimens is approximately 1/6 of a typical steel-concrete composite bridge beam (Figure 1). In the literature, there are studies in which similarly scaled specimens are used [28,31,33]. Each steel-concrete composite beam is formed with an IPE140 steel section and a 350 mm wide, 50 mm thick site-cast concrete deck ( Figure 2). The length of the beams is 2800 mm. There are two 150 mm long reinforced concrete blocks on support zones at both ends of the beams ( Figure 3). Six mm thick stiffeners are used on both sides of the web of I-section at the regions on the concrete blocks at beam supports, and at the regions of load application points ( Figure 3). These stiffeners are manually welded to the bottom flange, top flange and web of the steel beams with 3 mm weld size (thickness). This detail is typically applied on many highway bridges and determines the fatigue category of the bridge in general. This type of detail is categorized as type C' in the fatigue categories of AASHTO LRFD [8]. Shear studs having 10 mm diameter and 30 mm length are used between the steel section and the concrete deck. These connectors are installed in pairs at every 75 mm along the beam. The transversal distance between the connectors is 40 mm (Figure 4). In the concrete deck, 6 mm diameter ribbed bars were used as rebars. These rebars are placed with 75 mm spacing in both of the longitudinal and transverse directions of the beam in the vertical center of the deck Sustainability 2020, 12, 283 5 of 23 ( Figure 5). The reinforcement ratio of the concrete deck is approximately 0.8%. The design of these specimens is also used in the study of Gunes et al. [62].
Sustainability 2020, 12, x FOR PEER REVIEW 5 of 24 of the longitudinal and transverse directions of the beam in the vertical center of the deck ( Figure 5). The reinforcement ratio of the concrete deck is approximately 0.8%. The design of these specimens is also used in the study of Gunes et al. [62].     of the longitudinal and transverse directions of the beam in the vertical center of the deck ( Figure 5). The reinforcement ratio of the concrete deck is approximately 0.8%. The design of these specimens is also used in the study of Gunes et al. [62].      of the longitudinal and transverse directions of the beam in the vertical center of the deck ( Figure 5). The reinforcement ratio of the concrete deck is approximately 0.8%. The design of these specimens is also used in the study of Gunes et al. [62].      of the longitudinal and transverse directions of the beam in the vertical center of the deck ( Figure 5). The reinforcement ratio of the concrete deck is approximately 0.8%. The design of these specimens is also used in the study of Gunes et al. [62].

Fabrication
The production and preparation of the specimens for the tests are carried out in compliance with the design parameters described above in detail. These processes consist of the following phases: sandblasting of steel section, cutting of steel beam with the desired length, welding of stiffeners and

Fabrication
The production and preparation of the specimens for the tests are carried out in compliance with the design parameters described above in detail. These processes consist of the following phases: sandblasting of steel section, cutting of steel beam with the desired length, welding of stiffeners and shear studs, production of the concrete deck and support blocks. Firstly, the steel sections are subjected to sandblasting process. After sandblasting, the beams are cut with 2.8 m length. The transverse stiffeners with 6 mm thickness are welded on both sides of the web of I-section (one stiffener/each side) at the regions on the concrete blocks at beam supports, and at the regions of load application points ( Figure 6). The welding process is performed manually. The weld size (thickness) is 3 mm. Shear studs having 10 mm diameter and 30 mm length are welded between the steel section and the concrete deck in order to ensure the combined behavior of this structural system. The welding application is done with a welding machine and a welding gun. The rebars used in the concrete deck is cut with the desired lengths in the workshop and bent according to the design. Prepared rebars are brought to the laboratory and placed in the wooden formworks ( Figure 7). Plastic spacers are used to ensure the necessary spacing between the formwork and rebars. Finally, the production stages are completed by pouring concrete into the prepared forms. Some shrinkage cracks are observed on the concrete decks of some specimens after the production.

Fabrication
The production and preparation of the specimens for the tests are carried out in compliance with the design parameters described above in detail. These processes consist of the following phases: sandblasting of steel section, cutting of steel beam with the desired length, welding of stiffeners and shear studs, production of the concrete deck and support blocks. Firstly, the steel sections are subjected to sandblasting process. After sandblasting, the beams are cut with 2.8 m length. The transverse stiffeners with 6 mm thickness are welded on both sides of the web of I-section (1 stiffener/each side) at the regions on the concrete blocks at beam supports, and at the regions of load application points ( Figure 6). The welding process is performed manually. The weld size (thickness) is 3 mm. Shear studs having 10 mm diameter and 30 mm length are welded between the steel section and the concrete deck in order to ensure the combined behavior of this structural system. The welding application is done with a welding machine and a welding gun. The rebars used in the concrete deck is cut with the desired lengths in the workshop and bent according to the design. Prepared rebars are brought to the laboratory and placed in the wooden formworks ( Figure 7). Plastic spacers are used to ensure the necessary spacing between the formwork and rebars. Finally, the production stages are completed by pouring concrete into the prepared forms. Some shrinkage cracks are observed on the concrete decks of some specimens after the production.

Fabrication
The production and preparation of the specimens for the tests are carried out in compliance with the design parameters described above in detail. These processes consist of the following phases: sandblasting of steel section, cutting of steel beam with the desired length, welding of stiffeners and shear studs, production of the concrete deck and support blocks. Firstly, the steel sections are subjected to sandblasting process. After sandblasting, the beams are cut with 2.8 m length. The transverse stiffeners with 6 mm thickness are welded on both sides of the web of I-section (1 stiffener/each side) at the regions on the concrete blocks at beam supports, and at the regions of load application points ( Figure 6). The welding process is performed manually. The weld size (thickness) is 3 mm. Shear studs having 10 mm diameter and 30 mm length are welded between the steel section and the concrete deck in order to ensure the combined behavior of this structural system. The welding application is done with a welding machine and a welding gun. The rebars used in the concrete deck is cut with the desired lengths in the workshop and bent according to the design. Prepared rebars are brought to the laboratory and placed in the wooden formworks ( Figure 7). Plastic spacers are used to ensure the necessary spacing between the formwork and rebars. Finally, the production stages are completed by pouring concrete into the prepared forms. Some shrinkage cracks are observed on the concrete decks of some specimens after the production.

Test Setup and Instrumentation
MTS 810 type test setup is used in the tests. The used test setup has ±250 kN load capacity, and ±300 mm displacement capacity. Four-point loading is done in the tests as two of the loads are acting on the supports, and the other two are acting on the load application points (Figure 8). Elastomeric rubber sheets are used in the supports, and between the load distribution beam and the concrete deck, in order to prevent local crushing on the deck and to more realistically represent the common practice.

Test Setup and Instrumentation
MTS 810 type test setup is used in the tests. The used test setup has ±250 kN load capacity, and ±300 mm displacement capacity. Four-point loading is done in the tests as two of the loads were acting on the supports, and the other two were acting on the load application points (Figure 8). Elastomeric rubber sheets are used in the supports, and between the load distribution beam and the concrete deck, in order to prevent local crushing on the deck and to more realistically represent the common practice. A load cell having 1000 kN capacity is used between the hydraulic jack and the load distribution beam. Transducers having capacities ranging from 25 to 100 mm are used to measure the displacement values at different points on the specimen. FLA-6-11-5L type (SS) strain gauge with 6 mm measuring length is used for the steel part, PL-60-11-3L type (SC) strain gauge with 60 mm measuring length is used for the reinforced concrete part, along the span and height of the specimen. In addition, PI-5-100 type with a measurement length of 100 mm and PI-2-50 type with a measurement length of 50 mm strain gauges are used to measure the average strain values in some regions. The locations of the used measuring instruments on the test specimen are presented in Figure  9. TDS 302 and 303 type static data acquisition systems are used in the tests where monotonic loading was applied. DRA 101-C type dynamic data acquisition system is used in the fatigue tests. MSR abbreviation (midspan region) is used for the region where SS.04 strain gauge is located ( Figure 9). FCR abbreviation (fatigue critical regions, see Figure 6) is used for the end regions where the stiffeners are welded to the bottom flange of the steel beam ( Figure 9). A load cell having 1000 kN capacity is used between the hydraulic jack and the load distribution beam. Transducers having capacities ranging from 25 to 100 mm are used to measure the displacement values at different points on the specimen. FLA-6-11-5L type (SS) strain gauge with 6 mm measuring length is used for the steel part, PL-60-11-3L type (SC) strain gauge with 60 mm measuring length is used for the reinforced concrete part, along the span and height of the specimen. In addition, PI-5-100 type with a measurement length of 100 mm and PI-2-50 type with a measurement length of 50 mm strain gauges are used to measure the average strain values in some regions. The locations of the used measuring instruments on the test specimen are presented in Figure 9. TDS 302 and 303 type static data acquisition systems are used in the tests where monotonic loading was applied. DRA 101-C type dynamic data acquisition system is used in the fatigue tests. MSR abbreviation (midspan region) is used for the region where SS.04 strain gauge is located ( Figure 9). FCR abbreviation (fatigue critical regions, see Figure 6) is used for the end regions where the stiffeners are welded to the bottom flange of the steel beam ( Figure 9).

Testing Configuration
Initially, the specimen GS is statically tested under monotonically increasing displacements. The stiffness, yield strength, ultimate capacity and load-deflection behavior of the specimen are determined by the monotonic test. Then, load-controlled cyclic loads are applied to the specimens GF1, GF2, GF3a, GF3b and GF4. Loading types, number of cycles, the formation of the fatigue cracks and strain ranges formed in MSR and FCR regions during the cyclic loading are presented in Table  2. The yield strain value of the steel is determined considering the data obtained from the material tests (εy = 0.0019 mm/mm). The average of the strain ranges in the fatigue critical regions is calculated and presented in order to compare the strain ranges in these regions of the specimens with and without fatigue fractures. Permanent deflection and deformations (strains) occurred in the specimen GF3a at the end of 1,200,000 cycles as a result of accidental overloading. The bottom flange of the steel beam yielded. It is observed that the deflection and strain ranges are changed under the same loading range when cyclic loading is continued. Thus, the specimen is renamed as GF3b after this point, and cyclic loading is continued in order to examine the fatigue behavior of the overloaded beams. Cyclic loading is continued with additional 4,000,000 cycles after overloading.
In the tests of specimens without fatigue fracture, at least 50% more of the threshold number of cycles (2,545,927) defined in AASHTO LRFD [8] for the fatigue category C' is targeted. The strain ranges (amplitudes) of the specimens are determined by targeting 60-30% of the yield strain in the fatigue critical regions (FCR). The amplitude of the other specimens is determined according to the presence of fatigue fracture during the test process.

Testing Configuration
Initially, the specimen GS is statically tested under monotonically increasing displacements. The stiffness, yield strength, ultimate capacity and load-deflection behavior of the specimen are determined by the monotonic test. Then, load-controlled cyclic loads are applied to the specimens GF1, GF2, GF3a, GF3b and GF4. Loading types, number of cycles, the formation of the fatigue cracks and strain ranges formed in MSR and FCR regions during the cyclic loading are presented in Table 2. The yield strain value of the steel is determined considering the data obtained from the material tests (ε y = 0.0019 mm/mm). The average of the strain ranges in the fatigue critical regions is calculated and presented in order to compare the strain ranges in these regions of the specimens with and without fatigue fractures. Permanent deflection and deformations (strains) occurred in the specimen GF3a at the end of 1,200,000 cycles as a result of accidental overloading. The bottom flange of the steel beam yielded. It is observed that the deflection and strain ranges are changed under the same loading range when cyclic loading is continued. Thus, the specimen is renamed as GF3b after this point, and cyclic loading is continued in order to examine the fatigue behavior of the overloaded beams. Cyclic loading is continued with additional 4,000,000 cycles after overloading.
In the tests of specimens without fatigue fracture, at least 50% more of the threshold number of cycles (2,545,927) defined in AASHTO LRFD [8] for the fatigue category C' is targeted. The strain ranges (amplitudes) of the specimens are determined by targeting 60-30% of the yield strain in the fatigue critical regions (FCR). The amplitude of the other specimens is determined according to the presence of fatigue fracture during the test process.

Specimen GS
In Figure 10a, load-deflection behavior of specimen GS is presented. In this specimen, yielding of steel beam occurred at 70.00 kN load and 12.54 mm midspan deflection values. The yield load is defined as the total load when the strain value is reached under the bottom flange of the steel beam. Crushing of concrete in the deck occurred at 97.00 kN load and 46.92 mm midspan deflection values, and the specimen reached its ultimate capacity. When 96.66 kN load and 47.34 mm midspan deflection values are reached in the midspan, the rebars in the concrete deck are buckled, and the specimen failed by losing its capacity. The total strength loss is calculated about 25% with the crushing of concrete and buckling of rebars in the deck. The load-strain curves of the section in the midspan are shown in Figure 10b. The initial neutral axis of the specimen was between the SS-06 and SS-07 strain gauges. As the load level increased, the neutral axis shifted into the region between the SS-07 and SS-08 strain gauges. The maximum strain occurred on the concrete deck is obtained at P = 97.00 kN and δ = 33.62 mm values, as −0.0030 mm/mm. Midspan deflection, crushing of concrete and buckling of rebars occurred at the end of the test of the specimen GS are presented in Figure 11.

Specimen GS
In Figure 10a, load-deflection behavior of specimen GS is presented. In this specimen, yielding of steel beam occurred at 70.00 kN load and 12.54 mm midspan deflection values. The yield load is defined as the total load when the strain value is reached under the bottom flange of the steel beam. Crushing of concrete in the deck occurred at 97.00 kN load and 46.92 mm midspan deflection values, and the specimen reached its ultimate capacity. When 96.66 kN load and 47.34 mm midspan deflection values are reached in the midspan, the rebars in the concrete deck are buckled, and the specimen failed by losing its capacity. The total strength loss is calculated about 25% with the crushing of concrete and buckling of rebars in the deck. The load-strain curves of the section in the midspan are shown in Figure 10b. The initial neutral axis of the specimen was between the SS-06 and SS-07 strain gauges. As the load level increased, the neutral axis shifted into the region between the SS-07 and SS-08 strain gauges. The maximum strain occurred on the concrete deck is obtained at P = 97.00 kN and δ = 33.62 mm values, as −0.0030 mm/mm. Midspan deflection, crushing of concrete and buckling of rebars occurred at the end of the test of the specimen GS are presented in Figure 11.

Specimen GF1
Cyclic loading is applied to the specimen GF1 with a minimum of 0.67 kN, a maximum of 50.64 kN, and a loading rate of 0.9 Hz. Under these loads, an average stress range of 218 MPa is observed on fatigue critical regions. A crack occurred at the number of 403,000 load cycles on the bottom flange of the steel beam (left edge of the stiffener on the right). As this crack propagated through the bottom flange and height of the web, the specimen lost its capacity at the end of 407,000 load cycles and collapsed. Midspan deflection, fatigue crack and fatigue fracture occurred at the end of the test of the specimen GF1 are presented in Figure 12.
The variation of the deflection range (Δδ) during cyclic loading, and the maximum and minimum deflections (δmax, δmin) obtained are shown in Figure 13a. From the beginning of the test until 403,000 cycles just before the formation of the crack, the maximum deflection, δmax, is increased from 9.35 mm to 9.74 mm, and the deflection range, Δδ, is increased from 8.89 mm to 9.14 mm. The increase in the maximum deflection and the deflection range is continued similarly through the test. The maximum deflection is increased to δmax = 10.50 mm, and the deflection range is increased to Δδ = 9.23 mm, at 406,800 cycles just before the collapse of the specimen. The permanent deflection of the specimen is found as δ = 42.94 mm at the end of the fatigue failure. The normalized stiffness of the specimen decreased to 0.96 just before the formation of the crack (Figure 13b).

Specimen GF1
Cyclic loading is applied to the specimen GF1 with a minimum of 0.67 kN, a maximum of 50.64 kN, and a loading rate of 0.9 Hz. Under these loads, an average stress range of 218 MPa is observed on fatigue critical regions. A crack occurred at the number of 403,000 load cycles on the bottom flange of the steel beam (left edge of the stiffener on the right). As this crack propagated through the bottom flange and height of the web, the specimen lost its capacity at the end of 407,000 load cycles and collapsed. Midspan deflection, fatigue crack and fatigue fracture occurred at the end of the test of the specimen GF1 are presented in Figure 12.
The variation of the deflection range (∆δ) during cyclic loading, and the maximum and minimum deflections (δ max , δ min ) obtained are shown in Figure 13a. From the beginning of the test until 403,000 cycles just before the formation of the crack, the maximum deflection, δ max , is increased from 9.35 mm to 9.74 mm, and the deflection range, ∆δ, is increased from 8.89 mm to 9.14 mm. The increase in the maximum deflection and the deflection range is continued similarly through the test. The maximum deflection is increased to δ max = 10.50 mm, and the deflection range is increased to ∆δ = 9.23 mm, at 406,800 cycles just before the collapse of the specimen. The permanent deflection of the specimen is found as δ = 42.94 mm at the end of the fatigue failure. The normalized stiffness of the specimen decreased to 0.96 just before the formation of the crack (Figure 13b).  In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 14. Up to 295,000 cycles, the strain range in these regions varied from 1130 to 1300 με. No significant change is observed on the strain range up to this number of cycles. After this number of cycles, the values obtained from the strain gauge SS.10 started to increase unlike the others, and this trend continued increasingly. At 360,000 cycles, the values obtained from the strain gauge SS.09 increased rapidly and exceeded the values obtained from SS.10 at 400,700 cycles. At 403,000 cycles, a fatigue crack is formed on the location of the strain gauge SS.09.  In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 14. Up to 295,000 cycles, the strain range in these regions varied from 1130 to 1300 με. No significant change is observed on the strain range up to this number of cycles. After this number of cycles, the values obtained from the strain gauge SS.10 started to increase unlike the others, and this trend continued increasingly. At 360,000 cycles, the values obtained from the strain gauge SS.09 increased rapidly and exceeded the values obtained from SS.10 at 400,700 cycles. At 403,000 cycles, a fatigue crack is formed on the location of the strain gauge SS.09. In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 14. Up to 295,000 cycles, the strain range in these regions varied from 1130 to 1300 µε. No significant change is observed on the strain range up to this number of cycles. After this number of cycles, the values obtained from the strain gauge SS.10 started to increase unlike the others, and this trend continued increasingly. At 360,000 cycles, the values obtained from the strain gauge SS.09 increased rapidly and exceeded the values obtained from SS.10 at 400,700 cycles.
At 403,000 cycles, a fatigue crack is formed on the location of the strain gauge SS.09. This fatigue crack is formed at the center of the strain gauge SS.09. After this point, the crack is propagated to the edges of the bottom flange, and the bottom flange is completely cracked. At the end of 407,000 cycles, the fatigue failure occurred by the propagation of the crack through the height of the web, and the specimen lost its capacity.

Specimen GF2
Cyclic loading is applied to the specimen GF2 with a minimum of 0.8 kN, a maximum of 42 kN, and a loading rate of 1.2 Hz. Under these loads, an average stress range of 182 MPa is observed on fatigue critical regions. A crack occurred at 572,400 cycles on the bottom flange of the steel beam (left edge of the stiffener on the left). As this crack propagated through the bottom flange and height of the web, the specimen lost its capacity at the end of 584,800 cycles and collapsed. This fatigue crack and its propagation is shown in Figure 15.
The variation of the deflection range (Δδ) during cyclic loading, and the maximum and minimum deflections (δmax, δmin) obtained are shown in Figure 16a. From the beginning of the test until 572,250 cycles just before the formation of the crack, the maximum deflection, δmax, is increased from 8.08 mm to 8.13 mm, and the deflection range, Δδ, is increased from 7.69 mm to 7.88 mm. No significant increase is observed on the values related to the maximum deflection and deflection range up to this number of cycles. With the formation of the fatigue crack, the values increased rapidly, and the maximum deflection value is increased to δmax = 9.54 mm and the deflection range is increased to Δδ = 7.96 mm at the end of 584,200 cycles just before the collapse of the specimen. The permanent deflection of the specimen is found as δ = 37.90 mm at the end of the test. There was no significant reduction in the normalized stiffness of the specimen until the formation of the crack. The stiffness value of the specimen decreased to 0.98 just before the formation of the crack. After the crack, the stiffness value also decreased rapidly to 0.94 just before the collapse of the specimen (Figure 16b).
In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 17

Specimen GF2
Cyclic loading is applied to the specimen GF2 with a minimum of 0.8 kN, a maximum of 42 kN, and a loading rate of 1.2 Hz. Under these loads, an average stress range of 182 MPa is observed on fatigue critical regions. A crack occurred at 572,400 cycles on the bottom flange of the steel beam (left edge of the stiffener on the left). As this crack propagated through the bottom flange and height of the web, the specimen lost its capacity at the end of 584,800 cycles and collapsed. This fatigue crack and its propagation is shown in Figure 15.
The variation of the deflection range (∆δ) during cyclic loading, and the maximum and minimum deflections (δ max , δ min ) obtained are shown in Figure 16a. From the beginning of the test until 572,250 cycles just before the formation of the crack, the maximum deflection, δ max , is increased from 8.08 mm to 8.13 mm, and the deflection range, ∆δ, is increased from 7.69 mm to 7.88 mm. No significant increase is observed on the values related to the maximum deflection and deflection range up to this number of cycles. With the formation of the fatigue crack, the values increased rapidly, and the maximum deflection value is increased to δ max = 9.54 mm and the deflection range is increased to ∆δ = 7.96 mm at the end of 584,200 cycles just before the collapse of the specimen. The permanent deflection of the specimen is found as δ = 37.90 mm at the end of the test. There was no significant reduction in the normalized stiffness of the specimen until the formation of the crack. The stiffness value of the specimen decreased to 0.98 just before the formation of the crack. After the crack, the stiffness value also decreased rapidly to 0.94 just before the collapse of the specimen (Figure 16b).
In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 17

Specimen GF3a
Cyclic loading is applied to the specimen GF3a with a minimum of 0.7 kN, a maximum of 35.1 kN, and a loading rate of 1.8 Hz. Under these loads, an average stress range of 159 MPa is observed on fatigue critical regions. At the end of 1,200,000 cycles, no fatigue cracks or collapse are observed and the specimen did not collapse due to the fatigue. The variation of the deflection range (∆δ) during cyclic loading, and the maximum and minimum deflections (δ max , δ min ) obtained are shown in Figure 18a. The maximum deflection and deflection range increased throughout the test. However, the increase rates were not at a significant level. From the beginning until the termination of the test, the maximum deflection, δ max , is increased from 7.35 mm to 7.60 mm, and the deflection range, ∆δ, is increased from 6.80 mm to 7.22 mm. The normalized stiffness of the specimen decreased throughout the test to 0.94 (Figure 18b).

Specimen GF3a
Cyclic loading is applied to the specimen GF3a with a minimum of 0.7 kN, a maximum of 35.1 kN, and a loading rate of 1.8 Hz. Under these loads, an average stress range of 159 MPa is observed on fatigue critical regions. At the end of 1,200,000 cycles, no fatigue cracks or collapse are observed and the specimen did not collapse due to the fatigue. The variation of the deflection range (Δδ) during cyclic loading, and the maximum and minimum deflections (δmax, δmin) obtained are shown in Figure  18a. The maximum deflection and deflection range increased throughout the test. However, the increase rates were not at a significant level. From the beginning until the termination of the test, the maximum deflection, δmax, is increased from 7.35 mm to 7.60 mm, and the deflection range, Δδ, is increased from 6.80 mm to 7.22 mm. The normalized stiffness of the specimen decreased throughout the test to 0.94 (Figure 18b). In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 19. When the strain range-number of cycles curves are viewed, it is seen that the values of strain range varied between 830-930 με. No significant change is observed in the strain range. The strain ranges in these regions continued on a similar trend throughout the test. This behavior shows that formation of the fatigue cracks has not been started until this stage.  In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 19. When the strain range-number of cycles curves are viewed, it is seen that the values of strain range varied between 830-930 µε. No significant change is observed in the strain range. The strain ranges in these regions continued on a similar trend throughout the test. This behavior shows that formation of the fatigue cracks has not been started until this stage.

Specimen GF3a
Cyclic loading is applied to the specimen GF3a with a minimum of 0.7 kN, a maximum of 35.1 kN, and a loading rate of 1.8 Hz. Under these loads, an average stress range of 159 MPa is observed on fatigue critical regions. At the end of 1,200,000 cycles, no fatigue cracks or collapse are observed and the specimen did not collapse due to the fatigue. The variation of the deflection range (Δδ) during cyclic loading, and the maximum and minimum deflections (δmax, δmin) obtained are shown in Figure  18a. The maximum deflection and deflection range increased throughout the test. However, the increase rates were not at a significant level. From the beginning until the termination of the test, the maximum deflection, δmax, is increased from 7.35 mm to 7.60 mm, and the deflection range, Δδ, is increased from 6.80 mm to 7.22 mm. The normalized stiffness of the specimen decreased throughout the test to 0.94 (Figure 18b). In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 19. When the strain range-number of cycles curves are viewed, it is seen that the values of strain range varied between 830-930 με. No significant change is observed in the strain range. The strain ranges in these regions continued on a similar trend throughout the test. This behavior shows that formation of the fatigue cracks has not been started until this stage. Figure 19. The change in the strain range of the specimen GF3a during cyclic loading. Figure 19. The change in the strain range of the specimen GF3a during cyclic loading.
At the end of 1,200,000 cycles, δ = 31.52 mm of permanent deflection occurred as a result of accidental overloading of the specimen GF3a. In addition, permanent strains of 2367, 791, 14459, 960 and 1883 µε occurred on the strain gauges SS.01, SS.02, SS.04, SS.09 and SS.10, respectively. After this point, the specimen is considered as a new specimen (GF3b), which is yielded due to the overloading. Cyclic loading is continued to examine the fatigue behavior of the beams in this situation.

Specimen GF3b
Cyclic loading is applied to the specimen GF3b with 400,000 cycles, a loading range of 33.87 kN, and a loading rate of 1.8 Hz. Although the applied loading range was almost the same as the GF3a specimen, the deflections and the strain range were reduced. At the end of 1,200,000 cycles, the deflection range of GF3a was ∆δ = 7.22 mm. On the other hand, the deflection range of GF3b at the same loading range was ∆δ = 5.24 mm. Similar differences are also observed on the strain ranges. In midspan and stiffener regions of specimen GF3a, at the end of 1,200,000 cycles, the strain range obtained from the strain gauges SS.01, SS.02, SS.04, SS.09 and SS.10 were 873, 879, 930, 890 and 849 µε, respectively. On the other hand, for the specimen GF3b at the same loading range, the strain range obtained from the same strain gauges were 767, 769, 792, 754 and 713 µε, respectively. The average stress range in the fatigue critical regions (FCR) of the specimen GF3a was 159 MPa, while the average stress range at the same loading range in the specimen GF3b was 142 MPa.
Although the loading range remained constant throughout the test of the specimen GF3b, the increase in deflection and strain ranges were more than the other specimens. If the deflection and strain ranges of 1,200,000 and 5,200,000 cycles are compared, it can be said that ∆δ = 5.24 mm deflection range is increased to ∆δ = 5.61 mm, and 713~792 µε strain range is increased to 740~807 µε by 30 µε of an increase rate (Figures 20a and 21). Accordingly, as can be seen in Figure 20b At the end of 1,200,000 cycles, δ = 31.52 mm of permanent deflection occurred as a result of accidental overloading of the specimen GF3a. In addition, permanent strains of 2367, 791, 14459, 960 and 1883 με occurred on the strain gauges SS.01, SS.02, SS.04, SS.09 and SS.10, respectively. After this point, the specimen is considered as a new specimen (GF3b), which is yielded due to the overloading. Cyclic loading is continued to examine the fatigue behavior of the beams in this situation.

Specimen GF3b
Cyclic loading is applied to the specimen GF3b with 400,000 cycles, a loading range of 33.87 kN, and a loading rate of 1.8 Hz. Although the applied loading range was almost the same as the GF3a specimen, the deflections and the strain range were reduced. At the end of 1,200,000 cycles, the deflection range of GF3a was Δδ = 7.22 mm. On the other hand, the deflection range of GF3b at the same loading range was Δδ = 5.24 mm. Similar differences are also observed on the strain ranges. In midspan and stiffener regions of specimen GF3a, at the end of 1,200,000 cycles, the strain range obtained from the strain gauges SS.01, SS.02, SS.04, SS.09 and SS.10 were 873, 879, 930, 890 and 849 με, respectively. On the other hand, for the specimen GF3b at the same loading range, the strain range obtained from the same strain gauges were 767, 769, 792, 754 and 713 με, respectively. The average stress range in the fatigue critical regions (FCR) of the specimen GF3a was 159 MPa, while the average stress range at the same loading range in the specimen GF3b was 142 MPa.
Although the loading range remained constant throughout the test of the specimen GF3b, the increase in deflection and strain ranges were more than the other specimens. If the deflection and strain ranges of 1,200,000 and 5,200,000 cycles are compared, it can be said that Δδ = 5.24 mm deflection range is increased to Δδ = 5.61 mm, and 713~792 με strain range is increased to 740~807 με by 30 με of an increase rate (Figures 20a and Figure 21). Accordingly, as can be seen in Figure 20b, the normalized stiffness of the specimen is decreased to 0.94 of its stiffness at 1,200,000 cycles. The strain ranges in all regions continued on a similar trend with respect to each other throughout the test. This situation indicates that there was no onset of fatigue in the specimen. At the end of the test, the permanent deflection value is increased from δ = 31.52 mm to δ = 32.

Specimen GF4
Cyclic loading is applied to the specimen GF4 with a minimum of 0.8 kN, a maximum of 26.8 kN, and a loading rate of 2.5 Hz. Under these loads, an average stress range of 121 MPa is observed on fatigue critical regions. No fatigue cracks are observed at the end of 4,438,000 cycles. The variation of the deflection range (Δδ) during cyclic loading, and the maximum and minimum deflections (δmax, δmin) obtained are shown in Figure 22a. In the related graph, the maximum deflection values showed fluctuations throughout the test. The maximum deflection (δmax), which was 5.90 mm at the beginning of the test, increased to 6.08 mm during the test and measured as 5.93 mm at the end of the test. The deflection range (Δδ), which was 5.40 mm at the beginning of the test, increased to 5.70 mm at 3,250,000 cycles. After this point, no significant change is observed on the deflection range until the end of the test. The normalized stiffness of the specimen decreased to 0.95 until 3,250,000 cycles and remained approximately the same after this point (Figure 22b). In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 23. The stress ranges are varied from 630 με to 750 με in these regions throughout the test, and no significant change is observed on the stress ranges. The maximum increase in the stress ranges is measured as 25 με with respect to the beginning of the test. The strain ranges in all regions continued on a similar trend with respect to each other throughout the test. This situation means that there was no onset of fatigue failure and crack in the specimen.

Specimen GF4
Cyclic loading is applied to the specimen GF4 with a minimum of 0.8 kN, a maximum of 26.8 kN, and a loading rate of 2.5 Hz. Under these loads, an average stress range of 121 MPa is observed on fatigue critical regions. No fatigue cracks are observed at the end of 4,438,000 cycles. The variation of the deflection range (∆δ) during cyclic loading, and the maximum and minimum deflections (δ max , δ min ) obtained are shown in Figure 22a. In the related graph, the maximum deflection values showed fluctuations throughout the test. The maximum deflection (δ max ), which was 5.90 mm at the beginning of the test, increased to 6.08 mm during the test and measured as 5.93 mm at the end of the test. The deflection range (∆δ), which was 5.40 mm at the beginning of the test, increased to 5.70 mm at 3,250,000 cycles. After this point, no significant change is observed on the deflection range until the end of the test. The normalized stiffness of the specimen decreased to 0.95 until 3,250,000 cycles and remained approximately the same after this point (Figure 22b).

Specimen GF4
Cyclic loading is applied to the specimen GF4 with a minimum of 0.8 kN, a maximum of 26.8 kN, and a loading rate of 2.5 Hz. Under these loads, an average stress range of 121 MPa is observed on fatigue critical regions. No fatigue cracks are observed at the end of 4,438,000 cycles. The variation of the deflection range (Δδ) during cyclic loading, and the maximum and minimum deflections (δmax, δmin) obtained are shown in Figure 22a. In the related graph, the maximum deflection values showed fluctuations throughout the test. The maximum deflection (δmax), which was 5.90 mm at the beginning of the test, increased to 6.08 mm during the test and measured as 5.93 mm at the end of the test. The deflection range (Δδ), which was 5.40 mm at the beginning of the test, increased to 5.70 mm at 3,250,000 cycles. After this point, no significant change is observed on the deflection range until the end of the test. The normalized stiffness of the specimen decreased to 0.95 until 3,250,000 cycles and remained approximately the same after this point (Figure 22b). In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 23. The stress ranges are varied from 630 με to 750 με in these regions throughout the test, and no significant change is observed on the stress ranges. The maximum increase in the stress ranges is measured as 25 με with respect to the beginning of the test. The strain ranges in all regions continued on a similar trend with respect to each other throughout the test. This situation means that there was no onset of fatigue failure and crack in the specimen. In midspan and stiffener regions, the variation of the strain range formed on the steel bottom flange during cyclic loading is shown in Figure 23. The stress ranges are varied from 630 µε to 750 µε in these regions throughout the test, and no significant change is observed on the stress ranges. The maximum increase in the stress ranges is measured as 25 µε with respect to the beginning of the test. The strain ranges in all regions continued on a similar trend with respect to each other throughout the test. This situation means that there was no onset of fatigue failure and crack in the specimen.

Discussion
The loading properties and the strain and stress ranges formed on midspan regions (MSR) (under the bottom flange) are given in Table 3. As can be seen in the table, cyclic loads are applied to the specimens with various loading rates varying between 0.9 and 2.5 Hz, and various loading ranges varying between 49.96 and 26.00 kN. Under the cyclic loading, the ratio of strain range to yield strain varies between 68%-39%. The strains are measured during the test under the steel bottom flange (SS.01, SS.02, SS.09 and SS.10) and under the top flange (SS.03 and SS.14) (see Figure 9). The data obtained from these measurements are presented in Table 4. The stress range formed on the fatigue critical points (FCR) at the tips of the welds where the stiffeners are connected to the bottom flange is obtained using these data. In the FCR regions of the specimens, a strain range of 0.57εy-0.32εy, and a stress range of 218-121 MPa occurred during cyclic loading. The strain and stress ranges in the FCR regions are considered as the average of the data collected from the four points on the right and left of the stiffeners.

Discussion
The loading properties and the strain and stress ranges formed on midspan regions (MSR) (under the bottom flange) are given in Table 3. As can be seen in the table, cyclic loads are applied to the specimens with various loading rates varying between 0.9 and 2.5 Hz, and various loading ranges varying between 49.96 and 26.00 kN. Under the cyclic loading, the ratio of strain range to yield strain varies between 68-39%. The strains are measured during the test under the steel bottom flange (SS.01, SS.02, SS.09 and SS.10) and under the top flange (SS.03 and SS.14) (see Figure 9). The data obtained from these measurements are presented in Table 4. The stress range formed on the fatigue critical points (FCR) at the tips of the welds where the stiffeners are connected to the bottom flange is obtained using these data. In the FCR regions of the specimens, a strain range of 0.57ε y -0.32ε y , and a stress range of 218-121 MPa occurred during cyclic loading. The strain and stress ranges in the FCR regions are considered as the average of the data collected from the four points on the right and left of the stiffeners. Fatigue failure occurs with three stages as the onset of fatigue, crack formation and fatigue fracture. Strain data are collected during cyclic loading at the points where the fatigue is expected to occur (SS.01, SS.02, SS.09 and SS.10). In the specimens with fatigue fracture, as cyclic loading continues, the strain range at any of these points begins to increase, unlike the others. The related point is assumed as the onset of fatigue. After the onset of fatigue, at this point or on the other side of the same stiffener, the strain values increase rapidly, and the fatigue crack occurs over time. The fatigue fracture occurs by the propagation of this crack through the bottom flange and the height of the web. If the strains at the points where fatigue is expected change similarly during cyclic loading, fatigue crack and fatigue fracture do not occur.
Fatigue test results of the specimens are summarized in Table 5. The onset of fatigue on GF1 and GF2 specimens that are subjected to cyclic loads with stress range of 218 and 182 MPa, are observed at the reach of 275,000 and 400,000 cycles, respectively. Fatigue crack occurred when approximately 45% more of this cycle number is reached. Fatigue fracture occurred shortly after the formation of the fatigue crack. Although the cycles of GF3a, GF3b and GF4 are reached to 4,438,000, 1,200,000 and 4,000,000 respectively, no onset of fatigue was observed. In Figure 24a,b, the stress range-number of cycles (S-N) data of the fatigue tests performed in this study and data of some relevant studies conducted on this subject are compared. As mentioned in the previous sections, the type of detail that the stiffeners are welded to the web and flanges of the steel beam is included in category C' according to AASHTO LRFD [8]. According to AASHTO, the fatigue threshold of category C' is 82.7 MPa, and the cycle number is 2,545,927. When S-N data of the specimens are compared, it is seen that the fatigue strength of specimens is above the one specified for category C'. It can be said that the code's safety margin is conservative and the code remains on the safe side.
Although the data of GF1 and GF2 specimens with cyclic loads applied at the stress ranges of 218 and 182 MPa in the fatigue critical regions are above the category C', these results are compatible with the ones obtained by Fisher et al. [9] and Albrecht and Friedland [63]. No onset of fatigue and fatigue fracture is observed in the GF4 and GF3b specimens' tests, where 4,438,000 and 4,000,000 cycles are reached in the stress range of 121 and 142 MPa. Although these specimens are loaded at a higher stress range and 1.6 times higher cycles than the fatigue threshold specified for category C', the test is terminated because no signs for the onset of fatigue are detected.
In the existing buildings, the vibration-based structural health monitoring techniques are generally used. In these techniques, the relation between the changes in the stiffness of the structure and the damages is aimed to be established. In the present study, it is observed that the change in the stiffness of the structure is not a determinant parameter for the prediction of fatigue damages. Thus, it is believed that it is not possible to determine the fatigue damages with the vibration-based monitoring techniques. Recently, strain-based monitoring systems have been used in some significant buildings. The results of the present study reveal that strain-based monitoring techniques should be used for the determination of fatigue damages. The critical point here is which detail should be monitored. In steel bridges with critical fatigue details specified in AASHTO LRFD [8], the fatigue details with the maximum stress range should be determined by calculations and these points should be monitored using strain-based methods. The shape of the crack that may occur in the fatigue critical details is shown in AASHTO LRFD [8]. The changes in strain should be monitored by installing strain gauges perpendicular to this crack. for category C'. It can be said that the code's safety margin is conservative and the code remains on the safe side. Although the data of GF1 and GF2 specimens with cyclic loads applied at the stress ranges of 218 and 182 MPa in the fatigue critical regions are above the category C', these results are compatible with the ones obtained by Fisher et al. [9] and Albrecht and Friedland [63]. No onset of fatigue and fatigue fracture is observed in the GF4 and GF3b specimens' tests, where 4,438,000 and 4,000,000 cycles are reached in the stress range of 121 and 142 MPa. Although these specimens are loaded at a higher stress range and 1.6 times higher cycles than the fatigue threshold specified for category C', the test is terminated because no signs for the onset of fatigue are detected.
In the existing buildings, the vibration-based structural health monitoring techniques are generally used. In these techniques, the relation between the changes in the stiffness of the structure and the damages is aimed to be established. In the present study, it is observed that the change in the stiffness of the structure is not a determinant parameter for the prediction of fatigue damages. Thus, it is believed that it is not possible to determine the fatigue damages with the vibration-based monitoring techniques. Recently, strain-based monitoring systems have been used in some significant buildings. The results of the present study reveal that strain-based monitoring techniques should be used for the determination of fatigue damages. The critical point here is which detail should be monitored. In steel bridges with critical fatigue details specified in AASHTO LRFD [8], the fatigue details with the maximum stress range should be determined by calculations and these points should be monitored using strain-based methods. The shape of the crack that may occur in the fatigue critical details is shown in AASHTO LRFD [8]. The changes in strain should be monitored by installing strain gauges perpendicular to this crack.
The main factor that determines the fatigue behavior is the stress/strain range in the fatigue critical detail of the steel beam. The reduction of the yield strength, modulus of elasticity of concrete and compressive strength of concrete are not directly related to fatigue behavior. However, the effect of these factors on the stress range formed in the fatigue critical details has a significance. Although different failure modes caused by the connection details between concrete deck and steel beam are not directly related to fatigue behavior, they may be effective on fatigue behavior by changing the stress range in the fatigue critical details.
The effect of scale is not examined in this study. In Figure 24a,b, some important studies in the literature are shown which are also used in the determination of fatigue category C' in AASHTO LRFD [8]. The cross-sections used in the specimens of these studies have nearly real-scaled crosssections used in bridges. In the present study, smaller scaled specimens are used. However, as can be seen in these figures, the results of the present study are consistent with the results of AASHTO LRFD The main factor that determines the fatigue behavior is the stress/strain range in the fatigue critical detail of the steel beam. The reduction of the yield strength, modulus of elasticity of concrete and compressive strength of concrete are not directly related to fatigue behavior. However, the effect of these factors on the stress range formed in the fatigue critical details has a significance. Although different failure modes caused by the connection details between concrete deck and steel beam are not directly related to fatigue behavior, they may be effective on fatigue behavior by changing the stress range in the fatigue critical details.
The effect of scale is not examined in this study. In Figure 24a,b, some important studies in the literature are shown which are also used in the determination of fatigue category C' in AASHTO LRFD [8]. The cross-sections used in the specimens of these studies have nearly real-scaled cross-sections used in bridges. In the present study, smaller scaled specimens are used. However, as can be seen in these figures, the results of the present study are consistent with the results of AASHTO LRFD [8] and other important studies. There are also other studies in the literature in which fatigue tests are performed on similar small-scaled specimens.
The specimens without cracks and fatigue fractures after cyclic loading are monotonically loaded to determine the residual strength, and the results are compared with the reference specimen's (GS) which was not subjected to cyclic loads. Load-deflection curves of these specimens are presented in Figure 25. The points that represent the yielding of the steel beam and the crushing of concrete in the concrete deck are marked on these curves. The specimen GF4 is loaded with 4,438,000 cycles, and the specimen GF3 (GF3a and GF3b) is loaded with 5,200,000 cycles. The test of monotonic loading is started with δ = 32.28 mm permanent deflection caused by the accidental overloading of the specimen GF3 during cyclic loading. All specimens are collapsed due to the buckling of rebars after crushing of concrete in the deck. As a result of the monotonic loading at the end of cyclic loading, no significant decrease is observed in the stiffness, yield strength and ultimate capacity of the specimens. These results are consistent with the ones presented in the study of Yen et al. [33]. Cyclic loading did not cause a significant decrease in the ultimate strength. started with δ = 32.28 mm permanent deflection caused by the accidental overloading of the specimen GF3 during cyclic loading. All specimens are collapsed due to the buckling of rebars after crushing of concrete in the deck. As a result of the monotonic loading at the end of cyclic loading, no significant decrease is observed in the stiffness, yield strength and ultimate capacity of the specimens. These results are consistent with the ones presented in the study of Yen et al. [33]. Cyclic loading did not cause a significant decrease in the ultimate strength.

Conclusions
In this study, the data types that should be monitored during the service life of a bridge are investigated in order to predict the fatigue damages in steel-concrete composite bridges with welded full depth transverse stiffeners (fatigue-sensitive detail). In this context, the relationship between the fatigue damages and the variables such as deflection, stiffness and deformations (strains) during cyclic loading has been revealed by an experimental study.


The critical fatigue details of steel-concrete composite girder bridges that have reached or are at the end of their design life should be closely scrutinized. The structural safety and state of these bridges in terms of fatigue should be determined by strain-based measurements. The strains in the fatigue critical details should be monitored at regular intervals to check whether the onset of fatigue exists or not. Any increase in the strain range of one of these details different than the others indicates the onset of fatigue.  The changes in deflection and stiffness are not sufficient parameters for the determination of fatigue life. The change in stiffness will be less effective if the systems with a higher degree of indeterminacy are considered. There is no significant reduction in stiffness and strength of beams which do not exhibit fatigue behavior after cyclic loading.  S-N data obtained from the specimens are above the limits defined for category C' in AASHTO LRFD [8]. This is an expected situation. The most unfavorable cases of the fatigue tests of the details are considered in defining the fatigue categories according to AASHTO LRFD [8]. In this respect, the code considers a conservative safety margin and remains on the safe side. The S-N data of the specimens are consistent with those of other studies in the literature.

Conclusions
In this study, the data types that should be monitored during the service life of a bridge are investigated in order to predict the fatigue damages in steel-concrete composite bridges with welded full depth transverse stiffeners (fatigue-sensitive detail). In this context, the relationship between the fatigue damages and the variables such as deflection, stiffness and deformations (strains) during cyclic loading has been revealed by an experimental study.

•
The critical fatigue details of steel-concrete composite girder bridges that have reached or are at the end of their design life should be closely scrutinized. The structural safety and state of these bridges in terms of fatigue should be determined by strain-based measurements. The strains in the fatigue critical details should be monitored at regular intervals to check whether the onset of fatigue exists or not. Any increase in the strain range of one of these details different than the others indicates the onset of fatigue.

•
The changes in deflection and stiffness are not sufficient parameters for the determination of fatigue life. The change in stiffness will be less effective if the systems with a higher degree of indeterminacy are considered. There is no significant reduction in stiffness and strength of beams which do not exhibit fatigue behavior after cyclic loading. • S-N data obtained from the specimens are above the limits defined for category C' in AASHTO LRFD [8]. This is an expected situation. The most unfavorable cases of the fatigue tests of the details are considered in defining the fatigue categories according to AASHTO LRFD [8]. In this respect, the code considers a conservative safety margin and remains on the safe side. The S-N data of the specimens are consistent with those of other studies in the literature.

•
The vibration-based monitoring techniques, which are frequently used to determine the damage state of existing structures, are not sufficient to detect fatigue damages. In this study, it is found that the change in strain in fatigue critical details is determinant of fatigue behavior rather than the change in the stiffness. Thus, the fatigue details with the maximum stress range should be determined by calculations, and these points should be monitored using strain-based methods in steel bridges with critical fatigue details specified in AASHTO LRFD [8].
The future work offered by the authors about the scope of this paper consists of; performing full-scale tests to determine the effect of scale in future studies, and examining different proportions of weld thickness to the thickness of welded sheets in these tests; investigation of the effect of different damage types and strengthening methods on fatigue behavior; modelling of specimens by finite element method using various parameters, and examining the relationship between these parameters and test results.